GOE 491 AIRFOIL (goe491-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 491 AIRFOIL (goe491-il) Reynolds number: 200,000 Max Cl/Cd: 61.98 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe491-il-200000-n5.txt Download as CSV file: xf-goe491-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 491 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4491 0.09548 0.09196 -0.0077 1.0000 0.0239
-7.750 -0.4488 0.09279 0.08932 -0.0092 1.0000 0.0241
-7.500 -0.4504 0.09006 0.08665 -0.0111 1.0000 0.0244
-7.250 -0.4453 0.08689 0.08350 -0.0135 1.0000 0.0244
-7.000 -0.4386 0.08337 0.07998 -0.0167 1.0000 0.0246
-6.750 -0.4299 0.07974 0.07635 -0.0190 1.0000 0.0246
-6.500 -0.4197 0.07602 0.07262 -0.0211 1.0000 0.0247
-6.250 -0.4086 0.07216 0.06872 -0.0229 1.0000 0.0247
-5.750 -0.3921 0.06114 0.05765 -0.0242 1.0000 0.0139
-5.500 -0.3774 0.05847 0.05492 -0.0242 1.0000 0.0129
-5.250 -0.3649 0.05420 0.05057 -0.0252 1.0000 0.0125
-5.000 -0.3502 0.05013 0.04640 -0.0259 1.0000 0.0122
-4.750 -0.3342 0.04618 0.04233 -0.0262 1.0000 0.0120
-4.500 -0.3173 0.04218 0.03818 -0.0262 1.0000 0.0120
-4.250 -0.2998 0.03822 0.03402 -0.0257 1.0000 0.0121
-4.000 -0.2798 0.03520 0.03081 -0.0247 1.0000 0.0132
-3.750 -0.2627 0.03073 0.02606 -0.0235 0.9999 0.0135
-3.500 -0.2298 0.02416 0.01883 -0.0249 0.9955 0.0137
-3.250 -0.1993 0.01852 0.01225 -0.0252 0.9909 0.0141
-3.000 -0.1664 0.01540 0.00842 -0.0258 0.9871 0.0155
-2.750 -0.1332 0.01428 0.00704 -0.0267 0.9807 0.0191
-2.500 -0.0999 0.01314 0.00566 -0.0275 0.9737 0.0229
-2.250 -0.0656 0.01253 0.00502 -0.0287 0.9656 0.0312
-2.000 -0.0323 0.01237 0.00477 -0.0296 0.9561 0.0457
-1.750 -0.0001 0.01239 0.00468 -0.0305 0.9463 0.0570
-1.500 0.0356 0.01253 0.00473 -0.0321 0.9376 0.0682
-1.250 0.0713 0.01187 0.00404 -0.0337 0.9286 0.0715
-1.000 0.1069 0.01144 0.00359 -0.0352 0.9176 0.0745
-0.750 0.1438 0.01107 0.00318 -0.0370 0.9053 0.0780
-0.500 0.1804 0.01077 0.00281 -0.0387 0.8903 0.0816
-0.250 0.2150 0.01048 0.00252 -0.0400 0.8721 0.0871
0.000 0.2463 0.01032 0.00231 -0.0405 0.8493 0.0949
0.250 0.2755 0.01015 0.00212 -0.0406 0.8213 0.1045
0.500 0.3032 0.01003 0.00196 -0.0402 0.7878 0.1218
0.750 0.3282 0.00983 0.00187 -0.0394 0.7486 0.1933
1.250 0.4479 0.00847 0.00186 -0.0533 0.6366 1.0000
1.500 0.4690 0.00879 0.00188 -0.0517 0.5809 1.0000
1.750 0.4893 0.00918 0.00191 -0.0501 0.5181 1.0000
2.000 0.5104 0.00955 0.00198 -0.0486 0.4717 1.0000
2.250 0.5326 0.00986 0.00209 -0.0475 0.4394 1.0000
2.500 0.5560 0.01009 0.00223 -0.0465 0.4206 1.0000
2.750 0.5799 0.01029 0.00238 -0.0457 0.4061 1.0000
3.000 0.6039 0.01048 0.00254 -0.0449 0.3934 1.0000
3.250 0.6278 0.01067 0.00271 -0.0440 0.3785 1.0000
3.500 0.6518 0.01087 0.00292 -0.0432 0.3632 1.0000
3.750 0.6754 0.01109 0.00311 -0.0423 0.3425 1.0000
4.000 0.6986 0.01134 0.00330 -0.0414 0.3132 1.0000
4.250 0.7215 0.01164 0.00354 -0.0405 0.2773 1.0000
4.500 0.7437 0.01204 0.00380 -0.0394 0.2383 1.0000
4.750 0.7659 0.01246 0.00414 -0.0384 0.2042 1.0000
5.000 0.7874 0.01301 0.00455 -0.0373 0.1661 1.0000
5.250 0.8085 0.01362 0.00502 -0.0362 0.1233 1.0000
5.500 0.8277 0.01451 0.00566 -0.0348 0.0692 1.0000
5.750 0.8490 0.01512 0.00625 -0.0337 0.0553 1.0000
6.000 0.8706 0.01571 0.00689 -0.0325 0.0495 1.0000
6.250 0.8919 0.01630 0.00760 -0.0313 0.0440 1.0000
6.500 0.9115 0.01711 0.00849 -0.0300 0.0374 1.0000
6.750 0.9311 0.01790 0.00945 -0.0286 0.0317 1.0000
7.000 0.9498 0.01881 0.01051 -0.0271 0.0269 1.0000
7.250 0.9701 0.01952 0.01135 -0.0258 0.0204 1.0000
7.500 0.9859 0.02082 0.01275 -0.0239 0.0173 1.0000
7.750 1.0045 0.02179 0.01387 -0.0223 0.0146 1.0000
8.000 1.0235 0.02261 0.01480 -0.0210 0.0124 1.0000
8.250 1.0388 0.02402 0.01632 -0.0191 0.0111 1.0000
8.500 1.0489 0.02658 0.01907 -0.0165 0.0102 1.0000
8.750 1.0639 0.02846 0.02121 -0.0145 0.0097 1.0000
9.000 1.0785 0.03027 0.02337 -0.0127 0.0090 1.0000
9.250 1.0925 0.03180 0.02513 -0.0110 0.0081 1.0000
9.500 1.1041 0.03360 0.02717 -0.0091 0.0076 1.0000
9.750 1.1133 0.03551 0.02932 -0.0071 0.0072 1.0000
10.000 1.1184 0.03787 0.03193 -0.0047 0.0070 1.0000
10.250 1.1186 0.04061 0.03497 -0.0021 0.0068 1.0000
10.500 1.1121 0.04357 0.03820 0.0010 0.0067 1.0000
10.750 1.1018 0.04641 0.04129 0.0043 0.0067 1.0000
11.000 1.0853 0.05004 0.04518 0.0066 0.0066 1.0000
11.250 1.0689 0.05402 0.04938 0.0072 0.0066 1.0000
11.750 1.0414 0.06324 0.05903 0.0038 0.0066 1.0000
12.250 1.0121 0.07631 0.07248 -0.0052 0.0067 1.0000
12.500 0.9936 0.08480 0.08114 -0.0111 0.0068 1.0000
12.750 0.9594 0.09837 0.09493 -0.0199 0.0072 1.0000
13.000 0.9224 0.11426 0.11089 -0.0286 0.0076 1.0000
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Polar data table (+)
Polar graphs
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