AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AS5045 (15%) (as5045-il) Reynolds number: 200,000 Max Cl/Cd: 56.6 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5045-il-200000-n5.txt Download as CSV file: xf-as5045-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6112 0.11480 0.11120 -0.0129 1.0000 0.0131
-13.000 -0.6215 0.10631 0.10272 -0.0175 1.0000 0.0130
-12.750 -0.6383 0.09656 0.09291 -0.0236 1.0000 0.0128
-12.500 -0.6596 0.08730 0.08355 -0.0300 1.0000 0.0127
-12.250 -0.6813 0.07964 0.07576 -0.0353 0.9135 0.0126
-12.000 -0.6999 0.07259 0.06832 -0.0405 0.8503 0.0125
-11.750 -0.7184 0.06710 0.06255 -0.0431 0.8309 0.0124
-11.500 -0.7352 0.06219 0.05737 -0.0449 0.8195 0.0124
-11.250 -0.7496 0.05778 0.05270 -0.0460 0.8112 0.0123
-11.000 -0.7615 0.05376 0.04841 -0.0467 0.8043 0.0123
-10.750 -0.7702 0.05014 0.04449 -0.0468 0.7987 0.0123
-10.500 -0.7752 0.04683 0.04090 -0.0467 0.7937 0.0123
-10.250 -0.7777 0.04397 0.03773 -0.0459 0.7891 0.0123
-10.000 -0.7737 0.04120 0.03460 -0.0452 0.7851 0.0124
-9.750 -0.7655 0.03859 0.03160 -0.0444 0.7816 0.0127
-9.500 -0.7537 0.03626 0.02882 -0.0437 0.7781 0.0131
-9.250 -0.7373 0.03423 0.02658 -0.0433 0.7751 0.0134
-9.000 -0.7181 0.03263 0.02483 -0.0431 0.7724 0.0136
-8.750 -0.6975 0.03103 0.02303 -0.0427 0.7700 0.0138
-8.500 -0.6757 0.02953 0.02134 -0.0423 0.7678 0.0139
-8.250 -0.6531 0.02817 0.01983 -0.0419 0.7654 0.0141
-8.000 -0.6300 0.02692 0.01848 -0.0414 0.7628 0.0142
-7.750 -0.6069 0.02579 0.01725 -0.0410 0.7602 0.0145
-7.500 -0.5841 0.02475 0.01612 -0.0405 0.7579 0.0147
-7.250 -0.5615 0.02377 0.01508 -0.0400 0.7558 0.0151
-7.000 -0.5393 0.02286 0.01409 -0.0396 0.7539 0.0154
-6.750 -0.5171 0.02200 0.01316 -0.0392 0.7521 0.0159
-6.500 -0.4945 0.02119 0.01226 -0.0389 0.7502 0.0163
-6.250 -0.4720 0.02031 0.01137 -0.0389 0.7478 0.0169
-6.000 -0.4485 0.01955 0.01060 -0.0390 0.7455 0.0177
-5.750 -0.4236 0.01896 0.00996 -0.0392 0.7435 0.0192
-5.500 -0.3984 0.01835 0.00928 -0.0394 0.7416 0.0210
-5.250 -0.3726 0.01778 0.00866 -0.0397 0.7398 0.0228
-5.000 -0.3461 0.01729 0.00807 -0.0400 0.7380 0.0253
-4.750 -0.3195 0.01676 0.00748 -0.0403 0.7362 0.0304
-4.500 -0.2930 0.01606 0.00689 -0.0408 0.7343 0.0533
-4.250 -0.2710 0.01320 0.00564 -0.0434 0.7323 0.3649
-4.000 -0.2457 0.01276 0.00615 -0.0432 0.7304 0.5555
-3.750 -0.2174 0.01357 0.00701 -0.0425 0.7284 0.6139
-3.500 -0.1888 0.01405 0.00742 -0.0421 0.7262 0.6302
-3.250 -0.1598 0.01416 0.00743 -0.0423 0.7241 0.6357
-3.000 -0.1311 0.01432 0.00751 -0.0423 0.7224 0.6409
-2.750 -0.1009 0.01435 0.00737 -0.0429 0.7206 0.6478
-2.500 -0.0722 0.01443 0.00740 -0.0430 0.7187 0.6509
-2.250 -0.0434 0.01448 0.00743 -0.0432 0.7163 0.6539
-2.000 -0.0141 0.01451 0.00741 -0.0436 0.7137 0.6576
-1.750 0.0159 0.01449 0.00731 -0.0442 0.7111 0.6619
-1.500 0.0457 0.01447 0.00721 -0.0448 0.7086 0.6652
-1.250 0.0743 0.01450 0.00721 -0.0449 0.7061 0.6673
-1.000 0.1031 0.01454 0.00720 -0.0450 0.7039 0.6699
-0.750 0.1322 0.01456 0.00722 -0.0454 0.7005 0.6728
-0.500 0.1618 0.01454 0.00718 -0.0460 0.6969 0.6759
-0.250 0.1919 0.01450 0.00708 -0.0466 0.6933 0.6789
0.000 0.2214 0.01446 0.00700 -0.0471 0.6901 0.6810
0.250 0.2502 0.01446 0.00698 -0.0472 0.6871 0.6826
0.500 0.2789 0.01444 0.00701 -0.0475 0.6821 0.6843
0.750 0.3079 0.01440 0.00698 -0.0478 0.6775 0.6861
1.000 0.3371 0.01436 0.00691 -0.0481 0.6736 0.6882
1.250 0.3663 0.01433 0.00689 -0.0485 0.6689 0.6904
1.500 0.3957 0.01427 0.00687 -0.0489 0.6631 0.6924
1.750 0.4255 0.01419 0.00676 -0.0494 0.6581 0.6945
2.000 0.4549 0.01413 0.00672 -0.0498 0.6523 0.6965
2.250 0.4833 0.01404 0.00670 -0.0499 0.6452 0.6980
2.500 0.5120 0.01393 0.00662 -0.0500 0.6389 0.6995
2.750 0.5406 0.01386 0.00663 -0.0502 0.6298 0.7010
3.000 0.5694 0.01376 0.00657 -0.0504 0.6214 0.7026
3.250 0.5983 0.01366 0.00653 -0.0506 0.6112 0.7045
3.500 0.6271 0.01359 0.00652 -0.0509 0.5989 0.7066
3.750 0.6560 0.01350 0.00647 -0.0511 0.5850 0.7087
4.000 0.6848 0.01342 0.00638 -0.0513 0.5674 0.7106
4.250 0.7130 0.01336 0.00629 -0.0514 0.5444 0.7122
4.500 0.7395 0.01338 0.00622 -0.0511 0.5133 0.7135
4.750 0.7644 0.01357 0.00625 -0.0505 0.4747 0.7152
5.000 0.7885 0.01393 0.00643 -0.0500 0.4350 0.7170
5.250 0.8124 0.01436 0.00671 -0.0496 0.3978 0.7189
5.500 0.8362 0.01483 0.00706 -0.0492 0.3635 0.7207
5.750 0.8599 0.01533 0.00743 -0.0489 0.3317 0.7225
6.000 0.8835 0.01584 0.00783 -0.0486 0.3018 0.7244
6.250 0.9070 0.01637 0.00826 -0.0483 0.2739 0.7264
6.500 0.9295 0.01693 0.00874 -0.0479 0.2469 0.7283
6.750 0.9513 0.01750 0.00924 -0.0473 0.2223 0.7301
7.000 0.9734 0.01805 0.00974 -0.0468 0.2015 0.7319
7.250 0.9954 0.01860 0.01028 -0.0463 0.1831 0.7338
7.500 1.0170 0.01917 0.01083 -0.0457 0.1670 0.7357
7.750 1.0383 0.01977 0.01140 -0.0452 0.1522 0.7378
8.000 1.0591 0.02038 0.01202 -0.0446 0.1389 0.7399
8.250 1.0794 0.02103 0.01265 -0.0439 0.1271 0.7422
8.500 1.0983 0.02171 0.01334 -0.0431 0.1161 0.7444
8.750 1.1168 0.02238 0.01404 -0.0422 0.1061 0.7465
9.000 1.1346 0.02307 0.01480 -0.0412 0.0977 0.7489
9.250 1.1504 0.02389 0.01562 -0.0400 0.0901 0.7514
9.500 1.1661 0.02463 0.01644 -0.0388 0.0833 0.7539
9.750 1.1770 0.02555 0.01738 -0.0371 0.0779 0.7565
10.250 1.2030 0.02758 0.01955 -0.0348 0.0681 0.7616
10.500 1.2159 0.02868 0.02077 -0.0339 0.0643 0.7643
10.750 1.2282 0.02991 0.02209 -0.0332 0.0607 0.7673
11.000 1.2379 0.03141 0.02363 -0.0325 0.0575 0.7707
11.250 1.2494 0.03280 0.02514 -0.0320 0.0548 0.7745
11.500 1.2603 0.03420 0.02667 -0.0313 0.0521 0.7779
11.750 1.2693 0.03579 0.02837 -0.0307 0.0499 0.7818
12.000 1.2752 0.03768 0.03031 -0.0300 0.0479 0.7860
12.250 1.2842 0.03933 0.03209 -0.0294 0.0460 0.7906
12.500 1.2921 0.04101 0.03392 -0.0288 0.0442 0.7950
12.750 1.2989 0.04284 0.03587 -0.0282 0.0425 0.8003
13.000 1.3035 0.04490 0.03803 -0.0277 0.0411 0.8064
13.250 1.3046 0.04725 0.04046 -0.0270 0.0398 0.8130
13.500 1.3093 0.04933 0.04270 -0.0264 0.0386 0.8216
13.750 1.3130 0.05145 0.04502 -0.0259 0.0373 0.8326
14.000 1.3149 0.05370 0.04746 -0.0253 0.0361 0.8485
14.250 1.3136 0.05592 0.04989 -0.0242 0.0350 0.8835
14.500 1.3085 0.05828 0.05240 -0.0231 0.0342 1.0000
14.750 1.3075 0.06133 0.05552 -0.0233 0.0333 1.0000
15.000 1.3056 0.06459 0.05883 -0.0237 0.0325 1.0000
15.250 1.3064 0.06772 0.06215 -0.0242 0.0316 1.0000
15.500 1.3057 0.07113 0.06572 -0.0250 0.0306 1.0000
15.750 1.3038 0.07480 0.06953 -0.0260 0.0297 1.0000
16.000 1.3010 0.07872 0.07356 -0.0273 0.0288 1.0000
16.250 1.2972 0.08289 0.07784 -0.0287 0.0281 1.0000
16.500 1.2920 0.08733 0.08239 -0.0304 0.0275 1.0000
16.750 1.2856 0.09197 0.08710 -0.0322 0.0269 1.0000
17.000 1.2787 0.09694 0.09224 -0.0343 0.0263 1.0000
17.250 1.2709 0.10221 0.09770 -0.0366 0.0257 1.0000
17.500 1.2618 0.10778 0.10343 -0.0392 0.0251 1.0000
17.750 1.2522 0.11354 0.10936 -0.0421 0.0246 1.0000
18.000 1.2419 0.11956 0.11552 -0.0453 0.0241 1.0000
18.250 1.2314 0.12578 0.12187 -0.0487 0.0236 1.0000
18.500 1.2208 0.13212 0.12833 -0.0523 0.0232 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AS5045 (15%) (as5045-il)