EPPLER 336 AIRFOIL (e336-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 336 AIRFOIL (e336-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.74 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e336-il-1000000-n5.txt Download as CSV file: xf-e336-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 336 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4168 0.09207 0.08932 -0.0225 0.6518 0.0066
-8.500 -0.4996 0.06351 0.06054 -0.0316 0.5982 0.0063
-7.000 -0.5750 0.02597 0.02111 -0.0037 0.5626 0.0037
-6.750 -0.5657 0.02233 0.01696 -0.0003 0.5533 0.0036
-6.500 -0.5496 0.01975 0.01395 0.0020 0.5426 0.0036
-6.250 -0.5284 0.01821 0.01214 0.0033 0.5331 0.0035
-6.000 -0.5056 0.01688 0.01055 0.0044 0.5244 0.0035
-5.750 -0.4814 0.01597 0.00947 0.0052 0.5148 0.0035
-5.500 -0.4570 0.01508 0.00840 0.0060 0.5063 0.0035
-5.250 -0.4323 0.01435 0.00753 0.0067 0.4979 0.0035
-5.000 -0.4076 0.01371 0.00676 0.0074 0.4903 0.0035
-4.750 -0.3830 0.01315 0.00610 0.0081 0.4825 0.0035
-4.500 -0.3586 0.01266 0.00552 0.0089 0.4753 0.0036
-4.250 -0.3338 0.01228 0.00506 0.0096 0.4678 0.0036
-4.000 -0.3094 0.01189 0.00459 0.0104 0.4607 0.0036
-3.750 -0.2847 0.01156 0.00420 0.0111 0.4539 0.0036
-3.500 -0.2600 0.01127 0.00385 0.0118 0.4470 0.0037
-3.250 -0.2349 0.01101 0.00354 0.0124 0.4409 0.0037
-3.000 -0.2098 0.01078 0.00327 0.0131 0.4341 0.0038
-2.750 -0.1852 0.01052 0.00294 0.0138 0.4281 0.0040
-2.500 -0.1597 0.01033 0.00273 0.0144 0.4217 0.0044
-2.250 -0.1341 0.01020 0.00255 0.0149 0.4150 0.0047
-2.000 -0.1082 0.01008 0.00239 0.0154 0.4082 0.0056
-1.750 -0.0825 0.00996 0.00225 0.0159 0.3997 0.0069
-1.500 -0.0567 0.00986 0.00213 0.0164 0.3926 0.0098
-1.250 -0.0311 0.00975 0.00202 0.0169 0.3840 0.0179
-1.000 -0.0058 0.00961 0.00193 0.0174 0.3763 0.0354
-0.750 0.0184 0.00943 0.00185 0.0181 0.3664 0.0766
-0.500 0.0412 0.00915 0.00178 0.0190 0.3569 0.1517
-0.250 0.0251 0.00691 0.00140 0.0273 0.3523 0.6870
0.000 0.0342 0.00652 0.00168 0.0319 0.3471 0.8743
0.250 0.0603 0.00667 0.00179 0.0325 0.3420 0.8881
0.500 0.0857 0.00685 0.00191 0.0332 0.3383 0.8986
0.750 0.1139 0.00703 0.00207 0.0334 0.3356 0.9049
1.000 0.1410 0.00720 0.00221 0.0338 0.3328 0.9108
1.250 0.1666 0.00732 0.00229 0.0344 0.3300 0.9155
1.500 0.1946 0.00737 0.00230 0.0344 0.3277 0.9166
1.750 0.2225 0.00742 0.00231 0.0344 0.3256 0.9173
2.000 0.2503 0.00748 0.00233 0.0343 0.3230 0.9180
2.250 0.2784 0.00753 0.00235 0.0343 0.3214 0.9187
2.500 0.3064 0.00757 0.00237 0.0342 0.3198 0.9194
2.750 0.3343 0.00761 0.00240 0.0341 0.3183 0.9200
3.000 0.3621 0.00766 0.00243 0.0341 0.3166 0.9206
3.250 0.3897 0.00771 0.00247 0.0340 0.3145 0.9213
3.500 0.4172 0.00778 0.00252 0.0340 0.3123 0.9221
3.750 0.4446 0.00785 0.00258 0.0340 0.3103 0.9229
4.000 0.4717 0.00795 0.00265 0.0340 0.3076 0.9237
4.250 0.4992 0.00800 0.00270 0.0340 0.3060 0.9244
4.500 0.5270 0.00804 0.00276 0.0339 0.3045 0.9250
4.750 0.5547 0.00809 0.00281 0.0338 0.3024 0.9257
5.000 0.5822 0.00815 0.00287 0.0337 0.2999 0.9264
5.250 0.6094 0.00822 0.00294 0.0337 0.2968 0.9270
5.500 0.6365 0.00831 0.00303 0.0337 0.2938 0.9277
5.750 0.6635 0.00840 0.00312 0.0336 0.2909 0.9284
6.000 0.6911 0.00846 0.00320 0.0335 0.2886 0.9290
6.250 0.7184 0.00852 0.00328 0.0334 0.2846 0.9297
6.500 0.7454 0.00861 0.00337 0.0334 0.2800 0.9303
6.750 0.7724 0.00870 0.00346 0.0334 0.2755 0.9309
7.000 0.7994 0.00878 0.00356 0.0333 0.2686 0.9316
7.250 0.8258 0.00891 0.00367 0.0334 0.2600 0.9323
7.500 0.8516 0.00907 0.00381 0.0335 0.2507 0.9330
7.750 0.8774 0.00923 0.00397 0.0336 0.2432 0.9337
8.000 0.9023 0.00944 0.00416 0.0338 0.2347 0.9345
8.250 0.9275 0.00962 0.00435 0.0340 0.2271 0.9353
8.500 0.9520 0.00985 0.00457 0.0343 0.2190 0.9361
8.750 0.9761 0.01009 0.00480 0.0347 0.2096 0.9370
9.000 0.9999 0.01035 0.00505 0.0351 0.1990 0.9380
9.250 1.0227 0.01066 0.00533 0.0356 0.1871 0.9391
9.500 1.0448 0.01100 0.00564 0.0362 0.1750 0.9402
9.750 1.0659 0.01138 0.00598 0.0370 0.1620 0.9416
10.000 1.0858 0.01181 0.00636 0.0379 0.1483 0.9430
10.250 1.1056 0.01223 0.00675 0.0388 0.1368 0.9443
10.750 1.1412 0.01319 0.00765 0.0413 0.1122 0.9473
11.000 1.1565 0.01373 0.00815 0.0429 0.1002 0.9492
11.250 1.1701 0.01429 0.00869 0.0447 0.0890 0.9515
11.500 1.1822 0.01479 0.00919 0.0469 0.0810 0.9541
11.750 1.1916 0.01529 0.00970 0.0495 0.0743 0.9575
12.000 1.1974 0.01598 0.01038 0.0525 0.0657 0.9614
12.250 1.2069 0.01668 0.01110 0.0545 0.0599 0.9658
12.500 1.2160 0.01751 0.01195 0.0562 0.0532 0.9713
12.750 1.2294 0.01861 0.01307 0.0564 0.0467 0.9761
13.000 1.2444 0.01999 0.01447 0.0555 0.0407 0.9806
13.250 1.2603 0.02145 0.01597 0.0542 0.0361 0.9846
13.500 1.2756 0.02332 0.01789 0.0521 0.0315 0.9873
13.750 1.2884 0.02553 0.02014 0.0498 0.0278 0.9901
14.000 1.2998 0.02778 0.02245 0.0478 0.0250 0.9940
14.250 1.2997 0.03040 0.02512 0.0474 0.0228 1.0000
14.500 1.2960 0.03301 0.02779 0.0476 0.0208 1.0000
14.750 1.2924 0.03574 0.03059 0.0476 0.0198 1.0000
15.000 1.2842 0.03904 0.03395 0.0473 0.0178 1.0000
15.250 1.2760 0.04240 0.03737 0.0470 0.0161 1.0000
15.500 1.2671 0.04592 0.04097 0.0465 0.0151 1.0000
15.750 1.2565 0.04968 0.04479 0.0459 0.0133 1.0000
16.000 1.2531 0.05273 0.04793 0.0453 0.0140 1.0000
16.250 1.2484 0.05600 0.05130 0.0446 0.0144 1.0000
16.750 1.2267 0.06434 0.05976 0.0425 0.0117 1.0000
17.000 1.2180 0.06834 0.06383 0.0414 0.0108 1.0000
17.250 1.2051 0.07300 0.06853 0.0400 0.0093 1.0000
17.500 1.1979 0.07698 0.07258 0.0387 0.0087 1.0000
17.750 1.1934 0.08065 0.07634 0.0376 0.0092 1.0000
18.000 1.1843 0.08498 0.08073 0.0361 0.0080 1.0000
18.250 1.1765 0.08918 0.08499 0.0347 0.0075 1.0000
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Polar data table (+)
Polar graphs
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