EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1214 AIRFOIL (e1214-il) Reynolds number: 500,000 Max Cl/Cd: 78.3 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1214-il-500000.txt Download as CSV file: xf-e1214-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1214 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.9022 0.08941 0.08458 -0.0332 1.0000 0.0249
-17.000 -0.9015 0.08622 0.08135 -0.0344 1.0000 0.0254
-16.750 -0.8991 0.08337 0.07847 -0.0353 1.0000 0.0256
-16.500 -0.8989 0.08015 0.07519 -0.0365 1.0000 0.0260
-16.250 -0.8984 0.07709 0.07210 -0.0376 1.0000 0.0261
-16.000 -0.8981 0.07393 0.06887 -0.0387 1.0000 0.0265
-15.750 -0.9028 0.07035 0.06528 -0.0399 1.0000 0.0268
-15.500 -0.9073 0.06679 0.06170 -0.0412 1.0000 0.0271
-15.250 -0.9150 0.06287 0.05774 -0.0427 1.0000 0.0274
-15.000 -0.9240 0.05896 0.05378 -0.0440 1.0000 0.0278
-14.750 -0.9312 0.05528 0.05005 -0.0453 1.0000 0.0279
-14.500 -0.9411 0.05132 0.04602 -0.0467 1.0000 0.0283
-14.250 -0.9506 0.04737 0.04200 -0.0480 1.0000 0.0287
-14.000 -0.9596 0.04348 0.03802 -0.0493 1.0000 0.0291
-13.750 -0.9672 0.03971 0.03417 -0.0507 1.0000 0.0293
-13.500 -0.9736 0.03604 0.03041 -0.0520 1.0000 0.0297
-13.250 -0.9770 0.03278 0.02705 -0.0532 1.0000 0.0302
-13.000 -0.9876 0.02904 0.02322 -0.0544 1.0000 0.0308
-12.750 -0.9915 0.02651 0.02062 -0.0543 1.0000 0.0313
-12.500 -0.9946 0.02455 0.01860 -0.0532 1.0000 0.0322
-12.250 -0.9947 0.02317 0.01716 -0.0512 1.0000 0.0331
-12.000 -0.9956 0.02204 0.01597 -0.0484 1.0000 0.0343
-11.750 -1.0000 0.02102 0.01494 -0.0444 1.0000 0.0356
-11.500 -1.0026 0.02031 0.01420 -0.0399 1.0000 0.0373
-11.250 -1.0022 0.01958 0.01346 -0.0358 1.0000 0.0395
-11.000 -0.9983 0.01881 0.01270 -0.0322 1.0000 0.0434
-10.750 -0.9879 0.01787 0.01182 -0.0300 0.9983 0.0511
-10.500 -0.9555 0.01648 0.01058 -0.0324 0.9803 0.0719
-10.250 -0.9151 0.01521 0.00947 -0.0360 0.9419 0.0979
-10.000 -0.8609 0.01410 0.00841 -0.0421 0.8897 0.1266
-9.500 -0.8225 0.01329 0.00744 -0.0391 0.8038 0.1613
-9.250 -0.8027 0.01299 0.00710 -0.0376 0.7771 0.1774
-9.000 -0.7808 0.01277 0.00682 -0.0364 0.7542 0.1914
-8.750 -0.7576 0.01260 0.00658 -0.0354 0.7338 0.2037
-8.500 -0.7340 0.01242 0.00637 -0.0344 0.7152 0.2139
-8.250 -0.7090 0.01231 0.00618 -0.0337 0.6977 0.2224
-8.000 -0.6840 0.01219 0.00601 -0.0329 0.6820 0.2305
-7.750 -0.6582 0.01213 0.00584 -0.0323 0.6672 0.2376
-7.500 -0.6327 0.01204 0.00572 -0.0316 0.6528 0.2454
-7.250 -0.6058 0.01202 0.00560 -0.0312 0.6393 0.2526
-7.000 -0.5805 0.01194 0.00549 -0.0305 0.6263 0.2597
-6.750 -0.5534 0.01193 0.00541 -0.0301 0.6139 0.2659
-6.500 -0.5270 0.01188 0.00529 -0.0296 0.6022 0.2723
-6.250 -0.5005 0.01188 0.00526 -0.0291 0.5902 0.2790
-6.000 -0.4732 0.01190 0.00519 -0.0287 0.5792 0.2842
-5.750 -0.4464 0.01182 0.00503 -0.0282 0.5685 0.2888
-5.500 -0.4195 0.01172 0.00492 -0.0278 0.5587 0.2931
-5.250 -0.3923 0.01169 0.00483 -0.0274 0.5482 0.2971
-5.000 -0.3648 0.01167 0.00473 -0.0270 0.5385 0.3011
-4.750 -0.3371 0.01169 0.00464 -0.0267 0.5285 0.3043
-4.500 -0.3103 0.01151 0.00447 -0.0263 0.5198 0.3089
-4.250 -0.2829 0.01145 0.00439 -0.0260 0.5108 0.3131
-4.000 -0.2556 0.01146 0.00432 -0.0256 0.5021 0.3171
-3.750 -0.2275 0.01144 0.00425 -0.0254 0.4934 0.3210
-3.500 -0.2002 0.01141 0.00413 -0.0250 0.4846 0.3245
-3.250 -0.1728 0.01128 0.00402 -0.0247 0.4768 0.3288
-3.000 -0.1453 0.01124 0.00396 -0.0244 0.4689 0.3328
-2.750 -0.1178 0.01126 0.00391 -0.0241 0.4614 0.3368
-2.500 -0.0896 0.01124 0.00385 -0.0239 0.4538 0.3404
-2.250 -0.0621 0.01122 0.00376 -0.0236 0.4461 0.3440
-2.000 -0.0349 0.01113 0.00370 -0.0232 0.4393 0.3485
-1.750 -0.0072 0.01110 0.00366 -0.0230 0.4323 0.3530
-1.500 0.0202 0.01114 0.00364 -0.0227 0.4255 0.3575
-1.250 0.0484 0.01117 0.00362 -0.0225 0.4194 0.3614
-1.000 0.0758 0.01109 0.00356 -0.0222 0.4126 0.3662
-0.750 0.1027 0.01110 0.00354 -0.0218 0.4062 0.3712
-0.500 0.1305 0.01111 0.00355 -0.0216 0.4008 0.3762
-0.250 0.1585 0.01114 0.00354 -0.0214 0.3950 0.3811
0.000 0.1854 0.01113 0.00352 -0.0210 0.3892 0.3870
0.250 0.2124 0.01116 0.00355 -0.0206 0.3837 0.3930
0.500 0.2404 0.01116 0.00357 -0.0204 0.3786 0.3990
0.750 0.2679 0.01119 0.00358 -0.0202 0.3735 0.4049
1.000 0.2942 0.01123 0.00362 -0.0198 0.3684 0.4123
1.250 0.3217 0.01127 0.00367 -0.0195 0.3639 0.4202
1.500 0.3492 0.01126 0.00371 -0.0192 0.3593 0.4284
1.750 0.3760 0.01129 0.00375 -0.0189 0.3546 0.4376
2.000 0.4025 0.01139 0.00382 -0.0185 0.3499 0.4470
2.250 0.4292 0.01141 0.00391 -0.0181 0.3462 0.4586
2.500 0.4564 0.01142 0.00398 -0.0178 0.3424 0.4715
2.750 0.4831 0.01145 0.00405 -0.0175 0.3382 0.4867
3.000 0.5089 0.01150 0.00414 -0.0170 0.3341 0.5041
3.250 0.5343 0.01160 0.00428 -0.0164 0.3298 0.5238
3.500 0.5608 0.01158 0.00437 -0.0160 0.3267 0.5473
3.750 0.5867 0.01158 0.00448 -0.0155 0.3233 0.5750
4.000 0.6116 0.01158 0.00460 -0.0149 0.3198 0.6084
4.250 0.6357 0.01161 0.00474 -0.0140 0.3163 0.6464
4.500 0.6589 0.01170 0.00494 -0.0131 0.3124 0.6895
4.750 0.6826 0.01161 0.00508 -0.0121 0.3097 0.7403
5.000 0.7052 0.01152 0.00523 -0.0108 0.3065 0.8013
5.250 0.7321 0.01147 0.00544 -0.0102 0.3033 0.8807
5.500 0.7946 0.01178 0.00579 -0.0172 0.2987 0.9411
5.750 0.8405 0.01214 0.00611 -0.0208 0.2947 0.9663
6.000 0.8797 0.01232 0.00632 -0.0231 0.2918 0.9820
6.250 0.9219 0.01253 0.00653 -0.0260 0.2881 0.9918
6.750 0.9988 0.01302 0.00693 -0.0306 0.2810 1.0000
7.000 1.0181 0.01330 0.00719 -0.0291 0.2782 1.0000
7.250 1.0387 0.01345 0.00738 -0.0277 0.2761 1.0000
7.500 1.0592 0.01363 0.00758 -0.0263 0.2736 1.0000
7.750 1.0794 0.01382 0.00778 -0.0250 0.2711 1.0000
8.000 1.0993 0.01404 0.00798 -0.0235 0.2685 1.0000
8.250 1.1184 0.01431 0.00822 -0.0220 0.2657 1.0000
8.500 1.1371 0.01472 0.00858 -0.0205 0.2625 1.0000
8.750 1.1571 0.01490 0.00882 -0.0191 0.2608 1.0000
9.000 1.1767 0.01512 0.00908 -0.0176 0.2587 1.0000
9.250 1.1959 0.01535 0.00934 -0.0162 0.2564 1.0000
9.500 1.2145 0.01560 0.00960 -0.0146 0.2540 1.0000
9.750 1.2322 0.01588 0.00987 -0.0129 0.2517 1.0000
10.000 1.2489 0.01624 0.01020 -0.0112 0.2491 1.0000
10.250 1.2663 0.01669 0.01064 -0.0096 0.2465 1.0000
10.500 1.2812 0.01693 0.01095 -0.0075 0.2449 1.0000
10.750 1.2943 0.01721 0.01128 -0.0051 0.2429 1.0000
11.000 1.3077 0.01752 0.01163 -0.0028 0.2408 1.0000
11.250 1.3213 0.01785 0.01199 -0.0007 0.2386 1.0000
11.500 1.3349 0.01824 0.01240 0.0012 0.2364 1.0000
11.750 1.3484 0.01874 0.01287 0.0030 0.2340 1.0000
12.000 1.3631 0.01933 0.01346 0.0046 0.2313 1.0000
12.250 1.3757 0.01980 0.01402 0.0063 0.2297 1.0000
12.500 1.3883 0.02035 0.01464 0.0078 0.2276 1.0000
12.750 1.4006 0.02096 0.01530 0.0092 0.2252 1.0000
13.000 1.4128 0.02164 0.01602 0.0105 0.2230 1.0000
13.250 1.4244 0.02242 0.01681 0.0116 0.2208 1.0000
13.500 1.4362 0.02329 0.01765 0.0127 0.2182 1.0000
13.750 1.4480 0.02419 0.01861 0.0137 0.2161 1.0000
14.000 1.4577 0.02521 0.01973 0.0145 0.2142 1.0000
14.250 1.4675 0.02630 0.02090 0.0152 0.2121 1.0000
14.500 1.4770 0.02746 0.02212 0.0158 0.2098 1.0000
14.750 1.4858 0.02872 0.02341 0.0164 0.2076 1.0000
15.000 1.4941 0.03004 0.02473 0.0169 0.2052 1.0000
15.250 1.5034 0.03130 0.02599 0.0175 0.2025 1.0000
15.500 1.5080 0.03305 0.02788 0.0177 0.2006 1.0000
15.750 1.5124 0.03488 0.02979 0.0177 0.1982 1.0000
16.000 1.5166 0.03676 0.03174 0.0178 0.1957 1.0000
16.250 1.5206 0.03865 0.03367 0.0178 0.1934 1.0000
16.500 1.5243 0.04052 0.03553 0.0179 0.1905 1.0000
16.750 1.5265 0.04267 0.03775 0.0179 0.1881 1.0000
17.000 1.5240 0.04545 0.04065 0.0174 0.1855 1.0000
17.250 1.5230 0.04812 0.04342 0.0169 0.1829 1.0000
17.500 1.5206 0.05097 0.04630 0.0163 0.1798 1.0000
17.750 1.5218 0.05332 0.04862 0.0160 0.1769 1.0000
18.000 1.5150 0.05681 0.05223 0.0151 0.1740 1.0000
18.250 1.5077 0.06048 0.05602 0.0140 0.1710 1.0000
18.500 1.5006 0.06409 0.05968 0.0130 0.1677 1.0000
18.750 1.4969 0.06720 0.06277 0.0123 0.1643 1.0000
19.000 1.4888 0.07103 0.06671 0.0111 0.1617 1.0000
19.250 1.4761 0.07557 0.07136 0.0096 0.1583 1.0000
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