AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AS5045 (15%) (as5045-il) Reynolds number: 50,000 Max Cl/Cd: 29.23 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5045-il-50000-n5.txt Download as CSV file: xf-as5045-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6456 0.08770 0.08035 -0.0408 1.0000 0.0376
-11.250 -0.6588 0.08272 0.07528 -0.0431 1.0000 0.0375
-11.000 -0.6730 0.07806 0.07051 -0.0450 1.0000 0.0373
-10.750 -0.6869 0.07380 0.06612 -0.0463 1.0000 0.0372
-10.500 -0.7003 0.06995 0.06211 -0.0470 1.0000 0.0371
-10.250 -0.7129 0.06652 0.05851 -0.0469 1.0000 0.0371
-10.000 -0.7214 0.06328 0.05503 -0.0465 1.0000 0.0372
-9.750 -0.7255 0.06013 0.05158 -0.0459 1.0000 0.0374
-9.250 -0.7162 0.05412 0.04516 -0.0447 1.0000 0.0384
-9.000 -0.7054 0.05152 0.04244 -0.0441 1.0000 0.0391
-8.750 -0.6946 0.04907 0.03979 -0.0433 1.0000 0.0396
-8.500 -0.6833 0.04680 0.03732 -0.0421 1.0000 0.0400
-8.250 -0.6733 0.04486 0.03519 -0.0404 1.0000 0.0403
-8.000 -0.6655 0.04330 0.03347 -0.0381 0.9991 0.0407
-7.750 -0.6329 0.04104 0.03091 -0.0393 0.9864 0.0416
-7.500 -0.5979 0.03915 0.02880 -0.0401 0.9764 0.0428
-7.250 -0.5603 0.03769 0.02711 -0.0406 0.9689 0.0447
-7.000 -0.5248 0.03647 0.02585 -0.0409 0.9619 0.0480
-6.750 -0.4938 0.03538 0.02466 -0.0413 0.9539 0.0520
-6.500 -0.4646 0.03430 0.02336 -0.0417 0.9459 0.0556
-6.250 -0.4426 0.03289 0.02198 -0.0422 0.9371 0.0603
-6.000 -0.4190 0.03152 0.02051 -0.0431 0.9297 0.0687
-5.750 -0.4007 0.03008 0.01907 -0.0434 0.9217 0.0811
-5.500 -0.3862 0.02799 0.01742 -0.0439 0.9146 0.1200
-5.250 -0.3897 0.02598 0.01799 -0.0395 0.9071 0.4358
-5.000 -0.3657 0.02944 0.02151 -0.0341 0.9013 0.5981
-4.750 -0.3336 0.03355 0.02540 -0.0273 0.8979 0.6552
-4.500 -0.3091 0.03357 0.02511 -0.0267 0.8928 0.6689
-4.250 -0.2872 0.03337 0.02464 -0.0262 0.8873 0.6818
-4.000 -0.2585 0.03333 0.02433 -0.0261 0.8831 0.6914
-3.750 -0.2323 0.03314 0.02390 -0.0260 0.8789 0.7012
-3.500 -0.2150 0.03287 0.02344 -0.0253 0.8731 0.7124
-3.250 -0.1875 0.03278 0.02317 -0.0250 0.8689 0.7191
-3.000 -0.1643 0.03244 0.02262 -0.0252 0.8646 0.7287
-2.750 -0.1408 0.03236 0.02240 -0.0246 0.8599 0.7348
-2.500 -0.1230 0.03210 0.02200 -0.0242 0.8545 0.7438
-2.250 -0.0957 0.03198 0.02173 -0.0241 0.8504 0.7490
-2.000 -0.0722 0.03178 0.02141 -0.0242 0.8460 0.7560
-1.750 -0.0543 0.03169 0.02123 -0.0233 0.8403 0.7621
-1.500 -0.0295 0.03158 0.02102 -0.0233 0.8355 0.7674
-1.250 -0.0035 0.03140 0.02071 -0.0240 0.8314 0.7738
-1.000 0.0147 0.03142 0.02069 -0.0230 0.8252 0.7785
-0.750 0.0384 0.03138 0.02058 -0.0229 0.8199 0.7834
-0.500 0.0657 0.03127 0.02038 -0.0236 0.8155 0.7888
-0.250 0.0829 0.03135 0.02044 -0.0227 0.8086 0.7932
0.000 0.1079 0.03135 0.02040 -0.0227 0.8030 0.7971
0.250 0.1356 0.03132 0.02033 -0.0232 0.7981 0.8014
0.500 0.1527 0.03148 0.02047 -0.0228 0.7901 0.8062
0.750 0.1810 0.03147 0.02044 -0.0231 0.7848 0.8093
1.000 0.2000 0.03164 0.02064 -0.0223 0.7771 0.8131
1.250 0.2258 0.03171 0.02070 -0.0225 0.7703 0.8169
1.500 0.2496 0.03186 0.02086 -0.0227 0.7629 0.8208
1.750 0.2738 0.03198 0.02101 -0.0226 0.7551 0.8241
2.000 0.2978 0.03211 0.02118 -0.0223 0.7473 0.8274
2.250 0.3224 0.03223 0.02135 -0.0222 0.7388 0.8309
2.500 0.3457 0.03243 0.02160 -0.0221 0.7297 0.8345
2.750 0.3751 0.03246 0.02167 -0.0227 0.7216 0.8380
3.000 0.3946 0.03270 0.02200 -0.0218 0.7107 0.8412
3.250 0.4266 0.03252 0.02189 -0.0220 0.7038 0.8444
3.500 0.4462 0.03278 0.02226 -0.0214 0.6912 0.8481
3.750 0.4695 0.03294 0.02251 -0.0212 0.6794 0.8518
4.000 0.5011 0.03265 0.02231 -0.0212 0.6710 0.8550
4.250 0.5220 0.03271 0.02251 -0.0203 0.6578 0.8587
4.500 0.5436 0.03275 0.02268 -0.0196 0.6438 0.8627
4.750 0.5670 0.03271 0.02277 -0.0192 0.6296 0.8666
5.000 0.5908 0.03255 0.02278 -0.0186 0.6149 0.8704
5.250 0.6136 0.03230 0.02268 -0.0176 0.5998 0.8745
5.500 0.6379 0.03196 0.02250 -0.0168 0.5842 0.8791
6.000 0.6893 0.03095 0.02182 -0.0152 0.5510 0.8880
6.250 0.7138 0.03048 0.02150 -0.0142 0.5317 0.8929
6.500 0.7383 0.03011 0.02128 -0.0134 0.5092 0.8985
6.750 0.7675 0.02930 0.02054 -0.0123 0.4871 0.9040
7.000 0.7927 0.02894 0.02021 -0.0112 0.4595 0.9104
7.250 0.8175 0.02875 0.02000 -0.0102 0.4296 0.9172
7.500 0.8391 0.02890 0.02007 -0.0091 0.3987 0.9249
7.750 0.8584 0.02937 0.02047 -0.0081 0.3680 0.9341
8.000 0.8762 0.03008 0.02111 -0.0074 0.3390 0.9466
8.250 0.8942 0.03096 0.02191 -0.0071 0.3123 0.9670
8.500 0.9094 0.03199 0.02292 -0.0068 0.2873 1.0000
8.750 0.9254 0.03321 0.02404 -0.0067 0.2657 1.0000
9.000 0.9410 0.03457 0.02541 -0.0067 0.2444 1.0000
9.250 0.9570 0.03600 0.02682 -0.0069 0.2256 1.0000
9.500 0.9724 0.03751 0.02829 -0.0070 0.2083 1.0000
9.750 0.9881 0.03906 0.02984 -0.0072 0.1928 1.0000
10.000 1.0032 0.04069 0.03148 -0.0074 0.1784 1.0000
10.250 1.0187 0.04235 0.03320 -0.0075 0.1657 1.0000
10.500 1.0340 0.04405 0.03496 -0.0075 0.1544 1.0000
10.750 1.0501 0.04567 0.03652 -0.0075 0.1447 1.0000
11.000 1.0638 0.04758 0.03862 -0.0074 0.1351 1.0000
11.250 1.0778 0.04949 0.04060 -0.0073 0.1272 1.0000
11.500 1.0909 0.05145 0.04266 -0.0072 0.1201 1.0000
11.750 1.1028 0.05362 0.04498 -0.0070 0.1140 1.0000
12.000 1.1107 0.05605 0.04761 -0.0069 0.1082 1.0000
12.250 1.1254 0.05791 0.04938 -0.0066 0.1034 1.0000
12.500 1.1249 0.06134 0.05321 -0.0066 0.0994 1.0000
12.750 1.1259 0.06445 0.05654 -0.0067 0.0956 1.0000
13.000 1.1348 0.06668 0.05877 -0.0066 0.0920 1.0000
13.250 1.1318 0.07046 0.06277 -0.0069 0.0895 1.0000
13.500 1.1172 0.07553 0.06820 -0.0079 0.0877 1.0000
13.750 1.0992 0.08118 0.07415 -0.0095 0.0863 1.0000
14.000 1.0765 0.08774 0.08097 -0.0119 0.0852 1.0000
14.250 1.0449 0.09618 0.08967 -0.0158 0.0849 1.0000
14.500 0.9910 0.10991 0.10366 -0.0237 0.0859 1.0000
14.750 0.9134 0.13301 0.12681 -0.0380 0.0871 1.0000
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