AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AS5045 (15%) (as5045-il) Reynolds number: 100,000 Max Cl/Cd: 43.54 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5045-il-100000-n5.txt Download as CSV file: xf-as5045-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AS5045 (15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6103 0.09422 0.08918 -0.0301 1.0000 0.0239
-11.750 -0.6313 0.08622 0.08110 -0.0355 1.0000 0.0236
-11.500 -0.6529 0.07935 0.07410 -0.0398 1.0000 0.0233
-11.250 -0.6733 0.07351 0.06812 -0.0430 1.0000 0.0231
-11.000 -0.6920 0.06843 0.06287 -0.0451 1.0000 0.0229
-10.750 -0.7086 0.06396 0.05822 -0.0464 1.0000 0.0227
-10.500 -0.7232 0.05999 0.05405 -0.0470 1.0000 0.0225
-10.250 -0.7357 0.05649 0.05034 -0.0468 1.0000 0.0223
-10.000 -0.7436 0.05327 0.04688 -0.0461 1.0000 0.0221
-9.500 -0.7268 0.04615 0.03893 -0.0481 0.9047 0.0218
-9.250 -0.7105 0.04308 0.03539 -0.0487 0.8854 0.0218
-9.000 -0.6933 0.04050 0.03238 -0.0487 0.8724 0.0218
-8.750 -0.6740 0.03823 0.02974 -0.0485 0.8629 0.0219
-8.500 -0.6529 0.03619 0.02740 -0.0482 0.8552 0.0221
-8.250 -0.6301 0.03436 0.02531 -0.0478 0.8493 0.0224
-8.000 -0.6059 0.03270 0.02344 -0.0475 0.8442 0.0228
-7.750 -0.5812 0.03121 0.02178 -0.0471 0.8393 0.0233
-7.500 -0.5565 0.02997 0.02036 -0.0466 0.8348 0.0242
-7.250 -0.5325 0.02884 0.01910 -0.0461 0.8307 0.0255
-7.000 -0.5100 0.02777 0.01807 -0.0457 0.8263 0.0269
-6.750 -0.4875 0.02679 0.01705 -0.0452 0.8224 0.0282
-6.500 -0.4658 0.02583 0.01602 -0.0447 0.8190 0.0293
-6.250 -0.4444 0.02494 0.01502 -0.0442 0.8159 0.0305
-6.000 -0.4239 0.02396 0.01401 -0.0439 0.8125 0.0321
-5.750 -0.4020 0.02314 0.01311 -0.0437 0.8087 0.0344
-5.500 -0.3791 0.02240 0.01228 -0.0436 0.8053 0.0388
-5.250 -0.3558 0.02167 0.01151 -0.0435 0.8024 0.0467
-5.000 -0.3337 0.02066 0.01064 -0.0433 0.7999 0.0707
-4.750 -0.3257 0.01737 0.00952 -0.0438 0.7968 0.4182
-4.500 -0.3041 0.01875 0.01159 -0.0402 0.7936 0.5774
-4.250 -0.2785 0.02067 0.01344 -0.0375 0.7904 0.6304
-4.000 -0.2523 0.02143 0.01406 -0.0361 0.7878 0.6462
-3.750 -0.2253 0.02163 0.01410 -0.0355 0.7853 0.6527
-3.500 -0.1981 0.02173 0.01401 -0.0353 0.7829 0.6605
-3.250 -0.1708 0.02174 0.01390 -0.0354 0.7797 0.6672
-3.000 -0.1441 0.02183 0.01389 -0.0351 0.7767 0.6723
-2.750 -0.1151 0.02162 0.01351 -0.0363 0.7737 0.6804
-2.500 -0.0888 0.02170 0.01350 -0.0357 0.7708 0.6836
-2.250 -0.0618 0.02173 0.01343 -0.0355 0.7682 0.6878
-2.000 -0.0334 0.02163 0.01323 -0.0363 0.7652 0.6936
-1.750 -0.0056 0.02156 0.01309 -0.0368 0.7615 0.6979
-1.500 0.0210 0.02158 0.01307 -0.0366 0.7580 0.7010
-1.250 0.0485 0.02157 0.01299 -0.0368 0.7547 0.7048
-1.000 0.0777 0.02149 0.01280 -0.0375 0.7518 0.7096
-0.750 0.1055 0.02146 0.01275 -0.0381 0.7476 0.7133
-0.500 0.1319 0.02149 0.01278 -0.0380 0.7432 0.7159
-0.250 0.1593 0.02149 0.01274 -0.0381 0.7393 0.7190
0.000 0.1879 0.02146 0.01265 -0.0384 0.7359 0.7223
0.250 0.2167 0.02145 0.01263 -0.0394 0.7306 0.7260
0.500 0.2447 0.02144 0.01261 -0.0398 0.7255 0.7287
0.750 0.2720 0.02142 0.01258 -0.0397 0.7213 0.7309
1.000 0.2990 0.02145 0.01264 -0.0398 0.7160 0.7332
1.250 0.3263 0.02147 0.01269 -0.0400 0.7098 0.7359
1.500 0.3553 0.02139 0.01259 -0.0403 0.7050 0.7388
1.750 0.3836 0.02141 0.01265 -0.0410 0.6979 0.7416
2.000 0.4124 0.02135 0.01260 -0.0414 0.6916 0.7440
2.250 0.4395 0.02128 0.01256 -0.0412 0.6858 0.7460
2.500 0.4657 0.02128 0.01265 -0.0411 0.6774 0.7483
2.750 0.4947 0.02110 0.01248 -0.0410 0.6718 0.7505
3.000 0.5212 0.02110 0.01259 -0.0412 0.6616 0.7528
3.250 0.5504 0.02090 0.01240 -0.0414 0.6542 0.7555
3.500 0.5787 0.02078 0.01238 -0.0417 0.6435 0.7583
3.750 0.6053 0.02065 0.01236 -0.0416 0.6325 0.7605
4.000 0.6324 0.02040 0.01220 -0.0413 0.6222 0.7625
4.250 0.6595 0.02016 0.01207 -0.0410 0.6101 0.7645
4.500 0.6861 0.01999 0.01202 -0.0408 0.5954 0.7669
4.750 0.7132 0.01982 0.01194 -0.0407 0.5787 0.7696
5.000 0.7406 0.01968 0.01190 -0.0407 0.5582 0.7725
5.250 0.7688 0.01944 0.01167 -0.0407 0.5353 0.7751
5.500 0.7944 0.01927 0.01148 -0.0399 0.5067 0.7769
5.750 0.8191 0.01923 0.01133 -0.0391 0.4734 0.7791
6.000 0.8422 0.01944 0.01139 -0.0383 0.4364 0.7816
6.250 0.8642 0.01985 0.01165 -0.0375 0.3994 0.7846
6.500 0.8857 0.02040 0.01206 -0.0369 0.3646 0.7876
6.750 0.9072 0.02102 0.01255 -0.0364 0.3319 0.7905
7.000 0.9265 0.02164 0.01311 -0.0355 0.3028 0.7928
7.250 0.9455 0.02232 0.01371 -0.0346 0.2757 0.7953
7.750 0.9829 0.02381 0.01509 -0.0330 0.2280 0.8014
8.000 1.0010 0.02463 0.01586 -0.0323 0.2074 0.8051
8.250 1.0175 0.02547 0.01666 -0.0313 0.1897 0.8083
8.500 1.0334 0.02630 0.01751 -0.0302 0.1741 0.8117
9.000 1.0642 0.02812 0.01938 -0.0282 0.1473 0.8192
9.250 1.0776 0.02906 0.02038 -0.0269 0.1362 0.8231
9.500 1.0883 0.03008 0.02146 -0.0253 0.1269 0.8271
9.750 1.0994 0.03126 0.02267 -0.0241 0.1184 0.8320
10.000 1.1127 0.03243 0.02395 -0.0233 0.1101 0.8376
10.250 1.1209 0.03383 0.02535 -0.0221 0.1037 0.8433
10.500 1.1332 0.03507 0.02677 -0.0213 0.0968 0.8501
10.750 1.1412 0.03659 0.02833 -0.0203 0.0918 0.8575
11.000 1.1513 0.03798 0.02990 -0.0193 0.0866 0.8664
11.250 1.1591 0.03945 0.03150 -0.0182 0.0820 0.8776
11.500 1.1634 0.04109 0.03316 -0.0169 0.0786 0.8945
11.750 1.1679 0.04233 0.03467 -0.0149 0.0752 0.9463
12.000 1.1770 0.04410 0.03655 -0.0147 0.0715 1.0000
12.250 1.1854 0.04613 0.03860 -0.0148 0.0684 1.0000
12.500 1.1945 0.04817 0.04074 -0.0146 0.0657 1.0000
12.750 1.2032 0.05026 0.04300 -0.0144 0.0628 1.0000
13.000 1.2099 0.05247 0.04532 -0.0144 0.0603 1.0000
13.250 1.2149 0.05478 0.04767 -0.0143 0.0582 1.0000
13.500 1.2200 0.05719 0.05013 -0.0141 0.0563 1.0000
13.750 1.2234 0.05990 0.05309 -0.0141 0.0544 1.0000
14.000 1.2251 0.06276 0.05614 -0.0141 0.0526 1.0000
14.250 1.2256 0.06572 0.05925 -0.0144 0.0510 1.0000
14.500 1.2254 0.06873 0.06234 -0.0147 0.0495 1.0000
14.750 1.2260 0.07166 0.06533 -0.0151 0.0482 1.0000
15.000 1.2227 0.07527 0.06909 -0.0156 0.0471 1.0000
15.250 1.2139 0.07982 0.07392 -0.0168 0.0461 1.0000
15.500 1.2033 0.08479 0.07915 -0.0184 0.0452 1.0000
15.750 1.1911 0.09026 0.08485 -0.0206 0.0444 1.0000
16.000 1.1772 0.09626 0.09108 -0.0233 0.0436 1.0000
16.250 1.1614 0.10290 0.09793 -0.0267 0.0430 1.0000
16.500 1.1423 0.11052 0.10576 -0.0309 0.0425 1.0000
16.750 1.1154 0.12029 0.11577 -0.0368 0.0424 1.0000
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