WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Reynolds number: 500,000 Max Cl/Cd: 102.34 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w153-il-500000.txt Download as CSV file: xf-fx77w153-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-W-153 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3860 0.10526 0.10128 -0.0011 0.4656 0.0265
-9.500 -0.3887 0.09945 0.09547 -0.0054 0.4636 0.0266
-9.250 -0.3912 0.09365 0.08967 -0.0096 0.4616 0.0267
-9.000 -0.3929 0.08790 0.08391 -0.0140 0.4593 0.0267
-8.750 -0.3957 0.08324 0.07928 -0.0158 0.4569 0.0269
-8.500 -0.3953 0.07897 0.07502 -0.0189 0.4543 0.0270
-8.250 -0.3997 0.07316 0.06921 -0.0252 0.4524 0.0271
-8.000 -0.4037 0.06863 0.06463 -0.0279 0.4502 0.0272
-7.750 -0.4018 0.06440 0.06032 -0.0301 0.4479 0.0274
-7.500 -0.3976 0.06044 0.05626 -0.0317 0.4457 0.0276
-7.250 -0.3913 0.05663 0.05231 -0.0329 0.4435 0.0278
-7.000 -0.3834 0.05285 0.04839 -0.0336 0.4414 0.0281
-6.750 -0.3739 0.04902 0.04440 -0.0339 0.4398 0.0286
-6.500 -0.3632 0.04511 0.04029 -0.0337 0.4381 0.0291
-6.250 -0.3868 0.02862 0.02219 -0.0285 0.4389 0.0221
-6.000 -0.3682 0.02613 0.01947 -0.0275 0.4368 0.0217
-5.750 -0.3481 0.02379 0.01682 -0.0263 0.4347 0.0212
-5.500 -0.3263 0.02168 0.01436 -0.0251 0.4328 0.0208
-5.250 -0.3025 0.02005 0.01244 -0.0242 0.4309 0.0207
-5.000 -0.2772 0.01887 0.01102 -0.0235 0.4291 0.0208
-4.750 -0.2514 0.01796 0.00991 -0.0230 0.4272 0.0210
-4.500 -0.2251 0.01723 0.00903 -0.0224 0.4255 0.0214
-4.250 -0.1983 0.01658 0.00828 -0.0220 0.4242 0.0219
-4.000 -0.1711 0.01611 0.00770 -0.0216 0.4227 0.0225
-3.750 -0.1454 0.01541 0.00701 -0.0211 0.4212 0.0233
-3.500 -0.1184 0.01505 0.00664 -0.0208 0.4197 0.0246
-3.250 -0.0911 0.01475 0.00627 -0.0205 0.4184 0.0263
-3.000 -0.0656 0.01415 0.00567 -0.0199 0.4171 0.0288
-2.750 -0.0395 0.01371 0.00520 -0.0194 0.4157 0.0328
-2.500 -0.0121 0.01354 0.00499 -0.0192 0.4144 0.0362
-2.250 0.0152 0.01336 0.00481 -0.0190 0.4133 0.0390
-2.000 0.0433 0.01335 0.00477 -0.0189 0.4123 0.0419
-1.750 0.0709 0.01327 0.00467 -0.0188 0.4111 0.0444
-1.500 0.0986 0.01330 0.00466 -0.0187 0.4098 0.0470
-1.250 0.1268 0.01328 0.00462 -0.0186 0.4090 0.0493
-1.000 0.1544 0.01311 0.00446 -0.0184 0.4083 0.0515
-0.750 0.1822 0.01300 0.00435 -0.0183 0.4076 0.0544
-0.500 0.2102 0.01291 0.00427 -0.0182 0.4068 0.0596
-0.250 0.2376 0.01272 0.00421 -0.0180 0.4056 0.0814
0.000 0.2625 0.01220 0.00414 -0.0176 0.4043 0.2123
0.250 0.2859 0.01158 0.00411 -0.0170 0.4030 0.3962
0.500 0.3064 0.01090 0.00411 -0.0157 0.4018 0.6002
0.750 0.3529 0.01011 0.00438 -0.0190 0.4005 0.9160
1.000 0.4008 0.01038 0.00459 -0.0228 0.3990 0.9573
1.250 0.4393 0.01059 0.00472 -0.0248 0.3975 0.9729
1.500 0.4842 0.01082 0.00484 -0.0282 0.3956 0.9828
1.750 0.5358 0.01120 0.00512 -0.0332 0.3931 0.9916
2.000 0.5931 0.01115 0.00505 -0.0393 0.3916 0.9979
2.250 0.6297 0.01118 0.00506 -0.0412 0.3900 1.0000
2.500 0.6561 0.01125 0.00512 -0.0410 0.3887 1.0000
2.750 0.6824 0.01133 0.00518 -0.0407 0.3874 1.0000
3.000 0.7088 0.01142 0.00526 -0.0405 0.3860 1.0000
3.250 0.7351 0.01151 0.00532 -0.0402 0.3845 1.0000
3.500 0.7613 0.01159 0.00538 -0.0400 0.3830 1.0000
3.750 0.7876 0.01169 0.00545 -0.0397 0.3816 1.0000
4.000 0.8138 0.01182 0.00554 -0.0394 0.3802 1.0000
4.250 0.8400 0.01202 0.00570 -0.0392 0.3786 1.0000
4.500 0.8660 0.01228 0.00595 -0.0390 0.3770 1.0000
4.750 0.8919 0.01235 0.00606 -0.0387 0.3757 1.0000
5.000 0.9177 0.01243 0.00618 -0.0384 0.3741 1.0000
5.250 0.9435 0.01251 0.00628 -0.0380 0.3721 1.0000
5.500 0.9693 0.01259 0.00637 -0.0377 0.3700 1.0000
5.750 0.9951 0.01268 0.00646 -0.0374 0.3681 1.0000
6.000 1.0209 0.01278 0.00655 -0.0371 0.3663 1.0000
6.250 1.0466 0.01291 0.00667 -0.0368 0.3645 1.0000
6.500 1.0722 0.01321 0.00693 -0.0366 0.3622 1.0000
6.750 1.0972 0.01333 0.00712 -0.0362 0.3604 1.0000
7.000 1.1222 0.01343 0.00729 -0.0358 0.3584 1.0000
7.250 1.1472 0.01354 0.00745 -0.0354 0.3560 1.0000
7.500 1.1723 0.01360 0.00753 -0.0350 0.3534 1.0000
7.750 1.1974 0.01365 0.00758 -0.0346 0.3507 1.0000
8.000 1.2224 0.01378 0.00769 -0.0342 0.3480 1.0000
8.250 1.2467 0.01399 0.00792 -0.0338 0.3449 1.0000
8.500 1.2706 0.01398 0.00801 -0.0332 0.3416 1.0000
8.750 1.2948 0.01397 0.00807 -0.0327 0.3377 1.0000
9.000 1.3192 0.01396 0.00807 -0.0322 0.3341 1.0000
9.250 1.3429 0.01407 0.00816 -0.0316 0.3302 1.0000
9.500 1.3669 0.01406 0.00829 -0.0311 0.3255 1.0000
9.750 1.3910 0.01407 0.00836 -0.0306 0.3203 1.0000
10.000 1.4146 0.01411 0.00842 -0.0300 0.3155 1.0000
10.250 1.4384 0.01420 0.00859 -0.0296 0.3092 1.0000
10.750 1.4829 0.01449 0.00891 -0.0282 0.2961 1.0000
11.000 1.5024 0.01480 0.00918 -0.0271 0.2889 1.0000
11.250 1.5224 0.01514 0.00957 -0.0262 0.2822 1.0000
11.500 1.5399 0.01559 0.01001 -0.0249 0.2752 1.0000
11.750 1.5581 0.01600 0.01047 -0.0237 0.2688 1.0000
12.000 1.5755 0.01644 0.01095 -0.0225 0.2608 1.0000
12.250 1.5910 0.01697 0.01150 -0.0210 0.2525 1.0000
12.750 1.6149 0.01833 0.01288 -0.0175 0.2360 1.0000
13.000 1.6184 0.01926 0.01380 -0.0146 0.2293 1.0000
13.250 1.6267 0.02010 0.01471 -0.0127 0.2231 1.0000
13.500 1.6306 0.02136 0.01601 -0.0109 0.2155 1.0000
13.750 1.6348 0.02285 0.01756 -0.0097 0.2081 1.0000
14.000 1.6333 0.02514 0.01989 -0.0091 0.1984 1.0000
14.250 1.6285 0.02821 0.02302 -0.0094 0.1899 1.0000
14.500 1.6144 0.03269 0.02756 -0.0105 0.1833 1.0000
14.750 1.6031 0.03689 0.03185 -0.0113 0.1772 1.0000
15.000 1.5832 0.04197 0.03701 -0.0121 0.1723 1.0000
15.250 1.5596 0.04735 0.04246 -0.0128 0.1687 1.0000
15.500 1.5466 0.05151 0.04671 -0.0132 0.1619 1.0000
15.750 1.5222 0.05691 0.05216 -0.0138 0.1547 1.0000
16.000 1.4994 0.06228 0.05756 -0.0146 0.1459 1.0000
16.250 1.4743 0.06817 0.06345 -0.0156 0.1378 1.0000
16.500 1.4521 0.07381 0.06910 -0.0167 0.1304 1.0000
16.750 1.4354 0.07888 0.07419 -0.0177 0.1224 1.0000
17.000 1.4155 0.08443 0.07974 -0.0188 0.1130 1.0000
17.250 1.3947 0.09023 0.08551 -0.0201 0.1013 1.0000
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