WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 80-080 (fx80080-il) Reynolds number: 50,000 Max Cl/Cd: 33.62 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx80080-il-50000.txt Download as CSV file: xf-fx80080-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 80-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4679 0.10894 0.10211 -0.0249 1.0000 0.2099
-8.500 -0.4532 0.10440 0.09757 -0.0233 1.0000 0.2228
-8.250 -0.4448 0.10055 0.09376 -0.0223 1.0000 0.2351
-8.000 -0.4412 0.09731 0.09059 -0.0214 1.0000 0.2473
-7.750 -0.4401 0.09437 0.08774 -0.0205 1.0000 0.2603
-7.500 -0.4407 0.09162 0.08508 -0.0193 1.0000 0.2750
-7.250 -0.4456 0.08927 0.08284 -0.0177 1.0000 0.2912
-7.000 -0.4565 0.08736 0.08109 -0.0157 1.0000 0.3070
-6.750 -0.4429 0.08369 0.07745 -0.0131 1.0000 0.3299
-6.500 -0.4588 0.08232 0.07625 -0.0104 1.0000 0.3494
-6.250 -0.4559 0.07965 0.07366 -0.0068 1.0000 0.3773
-6.000 -0.4407 0.07657 0.07060 -0.0023 1.0000 0.4173
-5.750 -0.4149 0.07344 0.06740 0.0030 1.0000 0.4883
-4.500 -0.4343 0.04917 0.04211 -0.0364 1.0000 0.2096
-4.250 -0.3981 0.04295 0.03502 -0.0399 1.0000 0.1510
-4.000 -0.3713 0.03915 0.03058 -0.0406 1.0000 0.1365
-3.750 -0.3423 0.03590 0.02649 -0.0409 1.0000 0.1248
-3.500 -0.3167 0.03296 0.02312 -0.0405 1.0000 0.1214
-3.250 -0.2898 0.03056 0.02021 -0.0400 1.0000 0.1201
-3.000 -0.2626 0.02885 0.01790 -0.0393 1.0000 0.1261
-2.750 -0.2377 0.02699 0.01593 -0.0386 1.0000 0.1371
-2.500 -0.2123 0.02534 0.01417 -0.0374 1.0000 0.1469
-2.250 -0.1893 0.02402 0.01286 -0.0360 1.0000 0.1740
-2.000 -0.1643 0.02253 0.01150 -0.0349 1.0000 0.2160
-1.750 -0.1512 0.01830 0.01057 -0.0270 1.0000 1.0000
-1.500 -0.1294 0.01839 0.00989 -0.0262 1.0000 1.0000
-1.250 -0.1079 0.01851 0.00953 -0.0257 1.0000 1.0000
-1.000 -0.0861 0.01867 0.00930 -0.0254 1.0000 1.0000
-0.750 -0.0641 0.01887 0.00916 -0.0251 1.0000 1.0000
-0.500 -0.0420 0.01909 0.00906 -0.0249 1.0000 1.0000
-0.250 -0.0199 0.01935 0.00906 -0.0247 1.0000 1.0000
0.000 0.0022 0.01963 0.00913 -0.0245 1.0000 1.0000
0.250 0.0241 0.01995 0.00925 -0.0242 1.0000 1.0000
0.500 0.0459 0.02029 0.00943 -0.0241 1.0000 1.0000
0.750 0.0676 0.02066 0.00964 -0.0238 1.0000 1.0000
1.000 0.0891 0.02106 0.00993 -0.0236 1.0000 1.0000
1.250 0.1104 0.02149 0.01027 -0.0235 1.0000 1.0000
1.500 0.1315 0.02195 0.01066 -0.0233 1.0000 1.0000
1.750 0.1523 0.02245 0.01110 -0.0231 1.0000 1.0000
2.000 0.1730 0.02298 0.01160 -0.0229 1.0000 1.0000
2.250 0.1933 0.02355 0.01215 -0.0228 1.0000 1.0000
2.500 0.2134 0.02416 0.01277 -0.0226 1.0000 1.0000
2.750 0.2331 0.02482 0.01345 -0.0225 1.0000 1.0000
3.000 0.2524 0.02552 0.01419 -0.0224 1.0000 1.0000
3.250 0.2713 0.02628 0.01503 -0.0223 1.0000 1.0000
3.500 0.2897 0.02709 0.01592 -0.0223 1.0000 1.0000
3.750 0.3076 0.02798 0.01690 -0.0223 1.0000 1.0000
4.000 0.3250 0.02894 0.01796 -0.0224 1.0000 1.0000
4.250 0.3654 0.03056 0.01979 -0.0270 0.9889 1.0000
4.500 0.4276 0.03238 0.02199 -0.0353 0.9608 1.0000
4.750 0.4916 0.03379 0.02380 -0.0429 0.9278 1.0000
5.000 0.5649 0.03446 0.02506 -0.0503 0.8862 1.0000
5.250 0.6733 0.03228 0.02381 -0.0583 0.8236 1.0000
5.500 0.7858 0.02445 0.01733 -0.0573 0.7211 1.0000
5.750 0.7991 0.02377 0.01398 -0.0446 0.3080 1.0000
6.000 0.8161 0.02700 0.01619 -0.0425 0.2139 1.0000
6.250 0.8567 0.03011 0.01888 -0.0437 0.1618 1.0000
6.500 0.8942 0.03315 0.02196 -0.0443 0.1363 1.0000
6.750 0.9260 0.03660 0.02547 -0.0446 0.1202 1.0000
7.000 0.9490 0.03944 0.02897 -0.0429 0.1114 1.0000
7.250 0.9752 0.04363 0.03336 -0.0424 0.1073 1.0000
7.500 0.9910 0.04749 0.03785 -0.0401 0.1053 1.0000
7.750 0.9998 0.05100 0.04207 -0.0373 0.1026 1.0000
8.000 1.0069 0.05504 0.04665 -0.0348 0.1013 1.0000
8.250 1.0129 0.05978 0.05183 -0.0326 0.1038 1.0000
8.500 1.0270 0.06571 0.05785 -0.0317 0.1066 1.0000
8.750 1.0024 0.06979 0.06286 -0.0277 0.1148 1.0000
9.000 0.9968 0.07517 0.06857 -0.0263 0.1230 1.0000
9.250 0.9792 0.08096 0.07460 -0.0252 0.1314 1.0000
9.500 0.9626 0.08745 0.08130 -0.0254 0.1486 1.0000
9.750 0.9208 0.09187 0.08578 -0.0260 0.1505 1.0000
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Polar data table (+)
Polar graphs
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