EPPLER 636 AIRFOIL (e636-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 636 AIRFOIL (e636-il) Reynolds number: 500,000 Max Cl/Cd: 95.6 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e636-il-500000.txt Download as CSV file: xf-e636-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 636 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4345 0.10434 0.10222 -0.0006 1.0000 0.0172
-9.750 -0.4328 0.10042 0.09832 -0.0025 1.0000 0.0176
-9.500 -0.4362 0.09524 0.09318 -0.0063 1.0000 0.0186
-9.000 -0.3769 0.07657 0.07476 -0.0131 1.0000 0.0194
-8.750 -0.3673 0.07175 0.06982 -0.0167 0.8828 0.0197
-8.500 -0.3763 0.06789 0.06572 -0.0177 0.8157 0.0198
-8.250 -0.3992 0.06174 0.05946 -0.0226 0.7905 0.0197
-8.000 -0.4761 0.06382 0.06163 -0.0253 0.9205 0.0193
-7.750 -0.4726 0.06121 0.05865 -0.0247 0.8209 0.0196
-7.500 -0.4720 0.05849 0.05570 -0.0232 0.7806 0.0197
-7.250 -0.4676 0.05612 0.05314 -0.0219 0.7513 0.0200
-7.000 -0.4611 0.05371 0.05055 -0.0206 0.7281 0.0203
-6.750 -0.4534 0.05105 0.04771 -0.0194 0.7079 0.0208
-6.500 -0.4440 0.04832 0.04479 -0.0180 0.6902 0.0215
-6.250 -0.4332 0.04503 0.04123 -0.0163 0.6748 0.0231
-6.000 -0.4281 0.03979 0.03534 -0.0122 0.6640 0.0247
-5.750 -0.4164 0.03675 0.03220 -0.0111 0.6499 0.0253
-5.500 -0.4001 0.03502 0.03033 -0.0099 0.6356 0.0259
-5.250 -0.3826 0.03348 0.02864 -0.0087 0.6220 0.0267
-5.000 -0.3643 0.03171 0.02666 -0.0072 0.6091 0.0282
-4.750 -0.3502 0.02872 0.02302 -0.0036 0.5987 0.0321
-4.500 -0.3294 0.02699 0.02126 -0.0030 0.5869 0.0331
-4.250 -0.3079 0.02587 0.02001 -0.0021 0.5757 0.0346
-4.000 -0.2847 0.02495 0.01886 -0.0008 0.5646 0.0378
-3.750 -0.2651 0.02294 0.01650 0.0010 0.5549 0.0419
-3.500 -0.2414 0.02183 0.01531 0.0017 0.5446 0.0437
-3.250 -0.2165 0.02128 0.01460 0.0025 0.5342 0.0478
-3.000 -0.1841 0.01618 0.00857 0.0052 0.5271 0.0247
-2.750 -0.1565 0.01506 0.00733 0.0055 0.5179 0.0242
-2.500 -0.1296 0.01414 0.00632 0.0060 0.5090 0.0242
-2.250 -0.1037 0.01352 0.00559 0.0066 0.5005 0.0243
-2.000 -0.0786 0.01284 0.00486 0.0074 0.4919 0.0247
-1.750 -0.0551 0.01223 0.00417 0.0085 0.4848 0.0252
-1.500 -0.0309 0.01179 0.00372 0.0093 0.4771 0.0266
-1.250 -0.0060 0.01156 0.00342 0.0101 0.4701 0.0279
-1.000 0.0194 0.01129 0.00312 0.0108 0.4627 0.0292
-0.750 0.0449 0.01114 0.00287 0.0114 0.4561 0.0307
-0.500 0.0706 0.01093 0.00264 0.0121 0.4498 0.0346
-0.250 0.0955 0.01068 0.00247 0.0128 0.4437 0.0648
0.000 0.0897 0.00837 0.00220 0.0189 0.4399 0.6556
0.250 0.1808 0.00862 0.00326 0.0073 0.4300 0.9475
0.500 0.2412 0.00927 0.00376 0.0012 0.4230 0.9609
0.750 0.3358 0.00994 0.00426 -0.0119 0.4140 0.9780
1.000 0.3679 0.01002 0.00425 -0.0129 0.4088 0.9817
1.250 0.3992 0.01002 0.00421 -0.0136 0.4035 0.9844
1.500 0.4341 0.00997 0.00408 -0.0153 0.3985 0.9860
1.750 0.4678 0.00997 0.00401 -0.0166 0.3938 0.9880
2.000 0.5006 0.00993 0.00395 -0.0178 0.3891 0.9903
2.250 0.5321 0.00995 0.00391 -0.0187 0.3842 0.9927
2.500 0.5637 0.01001 0.00390 -0.0197 0.3799 0.9946
2.750 0.5974 0.00992 0.00383 -0.0210 0.3757 0.9963
3.000 0.6305 0.00989 0.00377 -0.0223 0.3713 0.9982
3.250 0.6630 0.00992 0.00373 -0.0235 0.3669 0.9999
3.500 0.6879 0.00997 0.00380 -0.0231 0.3631 1.0000
3.750 0.7120 0.01002 0.00386 -0.0224 0.3594 1.0000
4.000 0.7360 0.01009 0.00392 -0.0218 0.3557 1.0000
4.250 0.7596 0.01023 0.00400 -0.0212 0.3517 1.0000
4.500 0.7837 0.01031 0.00412 -0.0206 0.3482 1.0000
4.750 0.8078 0.01037 0.00422 -0.0200 0.3446 1.0000
5.000 0.8318 0.01046 0.00431 -0.0193 0.3409 1.0000
5.250 0.8554 0.01063 0.00444 -0.0187 0.3371 1.0000
5.500 0.8794 0.01073 0.00458 -0.0181 0.3336 1.0000
5.750 0.9034 0.01081 0.00471 -0.0174 0.3299 1.0000
6.000 0.9272 0.01092 0.00483 -0.0168 0.3259 1.0000
6.250 0.9505 0.01113 0.00500 -0.0161 0.3218 1.0000
6.500 0.9744 0.01118 0.00515 -0.0155 0.3177 1.0000
6.750 0.9982 0.01126 0.00527 -0.0149 0.3130 1.0000
7.000 1.0214 0.01143 0.00542 -0.0141 0.3086 1.0000
7.250 1.0448 0.01157 0.00563 -0.0135 0.3043 1.0000
7.500 1.0684 0.01167 0.00580 -0.0128 0.2999 1.0000
7.750 1.0914 0.01183 0.00597 -0.0121 0.2954 1.0000
8.000 1.1141 0.01201 0.00619 -0.0113 0.2906 1.0000
8.250 1.1374 0.01211 0.00638 -0.0106 0.2852 1.0000
8.500 1.1596 0.01231 0.00659 -0.0098 0.2799 1.0000
8.750 1.1823 0.01247 0.00683 -0.0090 0.2745 1.0000
9.000 1.2045 0.01264 0.00704 -0.0082 0.2672 1.0000
9.250 1.2265 0.01283 0.00728 -0.0074 0.2598 1.0000
9.500 1.2472 0.01309 0.00753 -0.0064 0.2500 1.0000
9.750 1.2688 0.01330 0.00780 -0.0055 0.2396 1.0000
10.000 1.2893 0.01359 0.00813 -0.0045 0.2287 1.0000
10.250 1.3087 0.01395 0.00850 -0.0033 0.2174 1.0000
10.500 1.3271 0.01438 0.00893 -0.0020 0.2041 1.0000
10.750 1.3435 0.01493 0.00945 -0.0005 0.1869 1.0000
11.000 1.3565 0.01568 0.01011 0.0014 0.1669 1.0000
11.250 1.3677 0.01651 0.01088 0.0036 0.1468 1.0000
11.500 1.3745 0.01754 0.01181 0.0063 0.1270 1.0000
11.750 1.3787 0.01862 0.01282 0.0093 0.1088 1.0000
12.000 1.3818 0.01965 0.01382 0.0125 0.0963 1.0000
12.250 1.3802 0.02070 0.01486 0.0164 0.0860 1.0000
12.500 1.3684 0.02182 0.01597 0.0217 0.0784 1.0000
12.750 1.3602 0.02328 0.01746 0.0252 0.0709 1.0000
13.000 1.3524 0.02533 0.01955 0.0272 0.0641 1.0000
13.250 1.3439 0.02801 0.02226 0.0281 0.0577 1.0000
13.500 1.3388 0.03075 0.02507 0.0284 0.0523 1.0000
13.750 1.3250 0.03460 0.02894 0.0282 0.0446 1.0000
14.000 1.3164 0.03806 0.03247 0.0279 0.0408 1.0000
14.250 1.2997 0.04249 0.03693 0.0273 0.0343 1.0000
14.500 1.2836 0.04694 0.04143 0.0266 0.0303 1.0000
14.750 1.2650 0.05177 0.04630 0.0257 0.0249 1.0000
15.000 1.2449 0.05687 0.05144 0.0247 0.0202 1.0000
15.250 1.2272 0.06185 0.05646 0.0235 0.0172 1.0000
15.500 1.2162 0.06621 0.06090 0.0224 0.0158 1.0000
15.750 1.2016 0.07116 0.06590 0.0210 0.0141 1.0000
16.000 1.1899 0.07585 0.07067 0.0197 0.0130 1.0000
16.250 1.1826 0.08000 0.07491 0.0185 0.0127 1.0000
16.500 1.1735 0.08446 0.07945 0.0171 0.0121 1.0000
16.750 1.1618 0.08941 0.08446 0.0155 0.0113 1.0000
17.000 1.1511 0.09428 0.08942 0.0139 0.0109 1.0000
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