E226 (10.19%) (e226-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E226 (10.19%) (e226-il) Reynolds number: 200,000 Max Cl/Cd: 59.61 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e226-il-200000.txt Download as CSV file: xf-e226-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E226 (10.19%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4669 0.10562 0.10227 -0.0126 1.0000 0.0631
-10.750 -0.4602 0.10237 0.09902 -0.0127 1.0000 0.0644
-8.000 -0.7178 0.03431 0.02835 -0.0327 1.0000 0.0312
-7.750 -0.7006 0.03319 0.02687 -0.0307 1.0000 0.0302
-7.500 -0.6873 0.02986 0.02328 -0.0290 1.0000 0.0296
-7.250 -0.6727 0.02721 0.02034 -0.0271 1.0000 0.0294
-7.000 -0.6559 0.02512 0.01798 -0.0252 1.0000 0.0293
-6.750 -0.6379 0.02340 0.01601 -0.0235 1.0000 0.0295
-6.500 -0.6195 0.02213 0.01456 -0.0218 1.0000 0.0303
-6.250 -0.6026 0.02016 0.01253 -0.0200 1.0000 0.0315
-6.000 -0.5852 0.01899 0.01135 -0.0183 1.0000 0.0327
-5.750 -0.5679 0.01796 0.01029 -0.0164 1.0000 0.0337
-5.500 -0.5510 0.01706 0.00933 -0.0144 1.0000 0.0351
-5.250 -0.5339 0.01628 0.00849 -0.0125 1.0000 0.0369
-5.000 -0.5164 0.01559 0.00773 -0.0107 1.0000 0.0391
-4.750 -0.4999 0.01470 0.00683 -0.0089 1.0000 0.0446
-4.500 -0.4827 0.01367 0.00597 -0.0072 1.0000 0.0742
-4.250 -0.4661 0.01252 0.00545 -0.0060 1.0000 0.1862
-4.000 -0.4470 0.01212 0.00526 -0.0049 1.0000 0.2434
-3.750 -0.4138 0.01168 0.00515 -0.0067 0.9960 0.3210
-3.500 -0.3753 0.01130 0.00507 -0.0094 0.9896 0.4041
-3.250 -0.3352 0.01099 0.00503 -0.0122 0.9838 0.4799
-3.000 -0.2988 0.01072 0.00495 -0.0141 0.9759 0.5401
-2.750 -0.2593 0.01051 0.00489 -0.0165 0.9699 0.5961
-2.500 -0.2232 0.01030 0.00484 -0.0180 0.9619 0.6456
-2.250 -0.1812 0.01013 0.00480 -0.0206 0.9571 0.6937
-2.000 -0.1472 0.00998 0.00474 -0.0215 0.9482 0.7358
-1.750 -0.1057 0.00984 0.00469 -0.0237 0.9434 0.7758
-1.500 -0.0744 0.00973 0.00465 -0.0238 0.9335 0.8100
-1.250 -0.0380 0.00963 0.00459 -0.0248 0.9266 0.8413
-1.000 -0.0071 0.00957 0.00456 -0.0246 0.9163 0.8699
-0.750 0.0248 0.00954 0.00453 -0.0245 0.9059 0.8952
-0.500 0.0613 0.00951 0.00447 -0.0254 0.8967 0.9159
-0.250 0.0991 0.00950 0.00442 -0.0267 0.8853 0.9333
0.000 0.1396 0.00950 0.00438 -0.0286 0.8729 0.9480
0.250 0.1825 0.00948 0.00431 -0.0312 0.8598 0.9601
0.500 0.2259 0.00945 0.00422 -0.0340 0.8454 0.9715
0.750 0.2725 0.00937 0.00410 -0.0376 0.8297 0.9809
1.000 0.3177 0.00929 0.00396 -0.0410 0.8124 0.9909
1.250 0.3613 0.00919 0.00379 -0.0442 0.7941 1.0000
1.500 0.3803 0.00915 0.00370 -0.0425 0.7731 1.0000
1.750 0.4001 0.00914 0.00362 -0.0410 0.7529 1.0000
2.000 0.4204 0.00916 0.00356 -0.0394 0.7326 1.0000
2.250 0.4410 0.00921 0.00355 -0.0379 0.7108 1.0000
2.500 0.4621 0.00929 0.00356 -0.0365 0.6896 1.0000
2.750 0.4834 0.00938 0.00360 -0.0351 0.6660 1.0000
3.000 0.5050 0.00951 0.00365 -0.0338 0.6429 1.0000
3.250 0.5267 0.00965 0.00372 -0.0324 0.6181 1.0000
3.500 0.5486 0.00981 0.00383 -0.0312 0.5921 1.0000
3.750 0.5706 0.01000 0.00395 -0.0299 0.5656 1.0000
4.000 0.5925 0.01022 0.00409 -0.0287 0.5377 1.0000
4.250 0.6144 0.01047 0.00426 -0.0274 0.5087 1.0000
4.500 0.6362 0.01073 0.00447 -0.0262 0.4781 1.0000
4.750 0.6577 0.01104 0.00468 -0.0249 0.4446 1.0000
5.000 0.6790 0.01139 0.00492 -0.0237 0.4102 1.0000
5.250 0.7006 0.01176 0.00522 -0.0225 0.3740 1.0000
5.500 0.7215 0.01221 0.00553 -0.0213 0.3358 1.0000
5.750 0.7421 0.01271 0.00588 -0.0201 0.2929 1.0000
6.000 0.7624 0.01329 0.00628 -0.0190 0.2466 1.0000
6.250 0.7825 0.01394 0.00675 -0.0179 0.2004 1.0000
6.500 0.8024 0.01466 0.00726 -0.0169 0.1576 1.0000
6.750 0.8223 0.01543 0.00786 -0.0158 0.1224 1.0000
7.000 0.8404 0.01647 0.00868 -0.0145 0.0771 1.0000
7.250 0.8533 0.01821 0.01017 -0.0122 0.0427 1.0000
7.500 0.8697 0.01945 0.01142 -0.0105 0.0355 1.0000
7.750 0.8876 0.02049 0.01252 -0.0090 0.0317 1.0000
8.000 0.9023 0.02195 0.01399 -0.0072 0.0295 1.0000
8.250 0.9187 0.02351 0.01562 -0.0056 0.0284 1.0000
8.500 0.9378 0.02488 0.01711 -0.0042 0.0274 1.0000
8.750 0.9573 0.02646 0.01881 -0.0030 0.0266 1.0000
9.000 0.9771 0.02825 0.02077 -0.0019 0.0261 1.0000
9.250 0.9961 0.03016 0.02287 -0.0007 0.0255 1.0000
9.500 1.0137 0.03201 0.02491 0.0004 0.0248 1.0000
9.750 1.0293 0.03360 0.02662 0.0017 0.0237 1.0000
10.000 1.0435 0.03579 0.02900 0.0029 0.0231 1.0000
10.250 1.0542 0.03846 0.03197 0.0046 0.0231 1.0000
10.500 1.0603 0.04139 0.03523 0.0066 0.0231 1.0000
10.750 1.0587 0.04485 0.03913 0.0093 0.0236 1.0000
11.000 1.0373 0.04900 0.04382 0.0135 0.0246 1.0000
11.250 1.0172 0.05283 0.04798 0.0164 0.0251 1.0000
11.500 0.9955 0.05701 0.05244 0.0177 0.0255 1.0000
11.750 0.9733 0.06162 0.05728 0.0175 0.0258 1.0000
12.000 0.9512 0.06683 0.06269 0.0158 0.0262 1.0000
12.250 0.9275 0.07303 0.06907 0.0125 0.0266 1.0000
12.500 0.9023 0.08043 0.07663 0.0075 0.0267 1.0000
12.750 0.8768 0.08912 0.08545 0.0012 0.0272 1.0000
13.000 0.8456 0.10059 0.09704 -0.0070 0.0276 1.0000
13.250 0.8224 0.11123 0.10770 -0.0135 0.0283 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E226 (10.19%) (e226-il)