WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Reynolds number: 500,000 Max Cl/Cd: 101.92 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w153-il-500000-n5.txt Download as CSV file: xf-fx77w153-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6692 0.04122 0.03656 -0.0355 0.4537 0.0122
-9.500 -0.6921 0.03321 0.02782 -0.0336 0.4525 0.0122
-9.250 -0.6855 0.02987 0.02403 -0.0320 0.4477 0.0122
-8.750 -0.6556 0.02560 0.01910 -0.0295 0.4383 0.0122
-8.500 -0.6363 0.02409 0.01732 -0.0285 0.4337 0.0123
-8.250 -0.6153 0.02282 0.01582 -0.0277 0.4294 0.0123
-8.000 -0.5931 0.02174 0.01453 -0.0269 0.4255 0.0123
-7.750 -0.5704 0.02070 0.01331 -0.0261 0.4224 0.0123
-7.500 -0.5471 0.01974 0.01217 -0.0254 0.4193 0.0124
-7.250 -0.5231 0.01892 0.01120 -0.0247 0.4162 0.0125
-7.000 -0.4986 0.01820 0.01034 -0.0241 0.4134 0.0126
-6.750 -0.4734 0.01759 0.00961 -0.0236 0.4107 0.0127
-6.500 -0.4479 0.01703 0.00896 -0.0231 0.4084 0.0128
-6.250 -0.4220 0.01653 0.00838 -0.0226 0.4063 0.0130
-6.000 -0.3958 0.01608 0.00786 -0.0222 0.4040 0.0132
-5.750 -0.3694 0.01568 0.00738 -0.0218 0.4020 0.0134
-5.500 -0.3427 0.01531 0.00695 -0.0214 0.4001 0.0136
-5.250 -0.3160 0.01498 0.00655 -0.0211 0.3984 0.0139
-5.000 -0.2891 0.01467 0.00618 -0.0208 0.3968 0.0142
-4.750 -0.2621 0.01439 0.00583 -0.0205 0.3953 0.0145
-4.500 -0.2350 0.01414 0.00552 -0.0202 0.3939 0.0150
-4.250 -0.2077 0.01391 0.00526 -0.0199 0.3927 0.0155
-4.000 -0.1800 0.01373 0.00509 -0.0197 0.3916 0.0164
-3.750 -0.1522 0.01357 0.00493 -0.0196 0.3904 0.0175
-3.500 -0.1244 0.01342 0.00476 -0.0194 0.3890 0.0190
-3.250 -0.0964 0.01330 0.00460 -0.0192 0.3876 0.0215
-3.000 -0.0684 0.01317 0.00444 -0.0191 0.3862 0.0233
-2.750 -0.0405 0.01305 0.00429 -0.0190 0.3850 0.0251
-2.500 -0.0124 0.01297 0.00416 -0.0189 0.3840 0.0265
-2.250 0.0151 0.01279 0.00396 -0.0187 0.3829 0.0279
-2.000 0.0429 0.01266 0.00381 -0.0186 0.3817 0.0296
-1.750 0.0708 0.01258 0.00368 -0.0185 0.3805 0.0312
-1.500 0.0985 0.01246 0.00355 -0.0183 0.3795 0.0331
-1.250 0.1264 0.01238 0.00346 -0.0182 0.3786 0.0346
-1.000 0.1544 0.01234 0.00339 -0.0181 0.3777 0.0359
-0.750 0.1824 0.01228 0.00333 -0.0181 0.3770 0.0373
-0.500 0.2105 0.01221 0.00329 -0.0180 0.3764 0.0407
-0.250 0.2386 0.01215 0.00324 -0.0180 0.3758 0.0465
0.000 0.2668 0.01209 0.00319 -0.0179 0.3747 0.0534
0.250 0.2948 0.01200 0.00316 -0.0178 0.3735 0.0649
0.500 0.3227 0.01191 0.00313 -0.0178 0.3723 0.0921
0.750 0.3499 0.01175 0.00312 -0.0177 0.3712 0.1403
1.000 0.3768 0.01154 0.00312 -0.0176 0.3703 0.2160
1.250 0.4033 0.01131 0.00313 -0.0174 0.3692 0.2979
1.500 0.4286 0.01097 0.00315 -0.0170 0.3681 0.4210
1.750 0.4506 0.01041 0.00316 -0.0160 0.3667 0.6061
2.000 0.4689 0.00960 0.00324 -0.0137 0.3653 0.8615
2.250 0.5427 0.00987 0.00358 -0.0231 0.3632 0.9569
2.500 0.5746 0.01006 0.00372 -0.0238 0.3617 0.9713
2.750 0.6088 0.01019 0.00383 -0.0251 0.3606 0.9806
3.000 0.6564 0.01030 0.00392 -0.0292 0.3593 0.9875
3.250 0.7194 0.01041 0.00401 -0.0367 0.3579 0.9973
3.500 0.7589 0.01048 0.00407 -0.0392 0.3567 1.0000
3.750 0.7852 0.01057 0.00415 -0.0390 0.3555 1.0000
4.000 0.8115 0.01066 0.00423 -0.0387 0.3542 1.0000
4.250 0.8376 0.01075 0.00431 -0.0385 0.3528 1.0000
4.500 0.8638 0.01085 0.00441 -0.0382 0.3515 1.0000
4.750 0.8898 0.01097 0.00451 -0.0379 0.3502 1.0000
5.000 0.9157 0.01110 0.00462 -0.0376 0.3488 1.0000
5.250 0.9414 0.01125 0.00475 -0.0373 0.3472 1.0000
5.500 0.9672 0.01140 0.00490 -0.0370 0.3456 1.0000
5.750 0.9931 0.01148 0.00502 -0.0367 0.3441 1.0000
6.000 1.0189 0.01158 0.00516 -0.0365 0.3426 1.0000
6.250 1.0446 0.01170 0.00532 -0.0361 0.3409 1.0000
6.500 1.0701 0.01181 0.00546 -0.0358 0.3390 1.0000
6.750 1.0956 0.01192 0.00560 -0.0355 0.3369 1.0000
7.000 1.1209 0.01205 0.00574 -0.0352 0.3349 1.0000
7.250 1.1460 0.01218 0.00589 -0.0348 0.3328 1.0000
7.500 1.1707 0.01234 0.00604 -0.0344 0.3304 1.0000
7.750 1.1962 0.01241 0.00620 -0.0341 0.3271 1.0000
8.000 1.2215 0.01250 0.00636 -0.0337 0.3230 1.0000
8.250 1.2464 0.01259 0.00647 -0.0333 0.3182 1.0000
8.500 1.2712 0.01268 0.00660 -0.0330 0.3121 1.0000
9.000 1.3188 0.01294 0.00682 -0.0319 0.2944 1.0000
9.250 1.3406 0.01323 0.00706 -0.0312 0.2855 1.0000
9.500 1.3622 0.01356 0.00739 -0.0304 0.2771 1.0000
9.750 1.3830 0.01393 0.00775 -0.0295 0.2696 1.0000
10.000 1.4036 0.01430 0.00813 -0.0287 0.2593 1.0000
10.250 1.4228 0.01475 0.00856 -0.0276 0.2492 1.0000
10.500 1.4403 0.01526 0.00906 -0.0263 0.2401 1.0000
10.750 1.4574 0.01579 0.00957 -0.0250 0.2324 1.0000
11.000 1.4733 0.01635 0.01013 -0.0235 0.2256 1.0000
11.250 1.4897 0.01686 0.01067 -0.0222 0.2179 1.0000
11.500 1.5031 0.01751 0.01133 -0.0204 0.2104 1.0000
11.750 1.5162 0.01817 0.01200 -0.0187 0.1997 1.0000
12.000 1.5236 0.01908 0.01289 -0.0164 0.1893 1.0000
12.250 1.5253 0.02012 0.01394 -0.0135 0.1813 1.0000
12.500 1.5282 0.02136 0.01520 -0.0113 0.1738 1.0000
12.750 1.5283 0.02310 0.01698 -0.0098 0.1661 1.0000
13.000 1.5221 0.02591 0.01982 -0.0093 0.1521 1.0000
13.250 1.5045 0.03079 0.02474 -0.0105 0.1384 1.0000
13.500 1.4858 0.03609 0.03012 -0.0119 0.1311 1.0000
13.750 1.4664 0.04131 0.03542 -0.0128 0.1261 1.0000
14.000 1.4475 0.04630 0.04049 -0.0135 0.1200 1.0000
14.500 1.4034 0.05677 0.05109 -0.0147 0.1078 1.0000
14.750 1.3799 0.06222 0.05657 -0.0153 0.1002 1.0000
15.000 1.3616 0.06732 0.06170 -0.0162 0.0953 1.0000
15.250 1.3461 0.07221 0.06660 -0.0170 0.0901 1.0000
15.500 1.3366 0.07639 0.07082 -0.0178 0.0835 1.0000
15.750 1.3228 0.08122 0.07566 -0.0187 0.0764 1.0000
16.000 1.3105 0.08589 0.08035 -0.0197 0.0656 1.0000
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