AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AS5046 (16%) (as5046-il) Reynolds number: 50,000 Max Cl/Cd: 28.05 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5046-il-50000-n5.txt Download as CSV file: xf-as5046-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AS5046 (16%)
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5615 0.10823 0.10086 -0.0358 1.0000 0.0414
-12.250 -0.5782 0.10039 0.09299 -0.0405 1.0000 0.0408
-12.000 -0.6006 0.09273 0.08526 -0.0451 1.0000 0.0402
-11.750 -0.6250 0.08593 0.07835 -0.0488 1.0000 0.0396
-11.500 -0.6488 0.08010 0.07239 -0.0514 1.0000 0.0392
-11.250 -0.6702 0.07512 0.06724 -0.0528 1.0000 0.0388
-11.000 -0.6884 0.07085 0.06278 -0.0533 1.0000 0.0386
-10.750 -0.7043 0.06712 0.05885 -0.0530 1.0000 0.0384
-10.500 -0.7175 0.06387 0.05540 -0.0519 1.0000 0.0382
-10.250 -0.7275 0.06095 0.05228 -0.0501 1.0000 0.0381
-10.000 -0.7312 0.05806 0.04914 -0.0485 1.0000 0.0381
-9.750 -0.7303 0.05531 0.04614 -0.0469 1.0000 0.0382
-9.500 -0.7255 0.05271 0.04331 -0.0453 1.0000 0.0384
-9.250 -0.7174 0.05029 0.04066 -0.0437 1.0000 0.0387
-9.000 -0.7070 0.04811 0.03829 -0.0421 1.0000 0.0393
-8.750 -0.6958 0.04621 0.03619 -0.0404 1.0000 0.0404
-8.500 -0.6848 0.04455 0.03432 -0.0385 1.0000 0.0416
-8.250 -0.6759 0.04324 0.03277 -0.0360 1.0000 0.0428
-8.000 -0.6665 0.04208 0.03158 -0.0334 1.0000 0.0440
-7.750 -0.6322 0.04051 0.03000 -0.0341 0.9950 0.0460
-7.500 -0.5907 0.03929 0.02866 -0.0348 0.9901 0.0483
-7.250 -0.5536 0.03834 0.02750 -0.0353 0.9829 0.0519
-7.000 -0.5262 0.03711 0.02632 -0.0358 0.9724 0.0564
-6.750 -0.5005 0.03596 0.02498 -0.0363 0.9614 0.0611
-6.500 -0.4804 0.03447 0.02351 -0.0369 0.9506 0.0671
-6.250 -0.4605 0.03297 0.02198 -0.0376 0.9416 0.0764
-6.000 -0.4414 0.03122 0.02033 -0.0384 0.9339 0.0936
-5.750 -0.4354 0.02883 0.01861 -0.0380 0.9243 0.1562
-5.500 -0.4247 0.02909 0.02139 -0.0316 0.9188 0.5027
-5.250 -0.4058 0.03125 0.02332 -0.0283 0.9110 0.5975
-5.000 -0.3764 0.03484 0.02671 -0.0231 0.9062 0.6532
-4.750 -0.3410 0.03530 0.02683 -0.0232 0.9025 0.6665
-4.500 -0.3106 0.03532 0.02656 -0.0232 0.8977 0.6765
-4.250 -0.2906 0.03505 0.02606 -0.0226 0.8914 0.6886
-4.000 -0.2606 0.03492 0.02569 -0.0230 0.8870 0.6980
-3.500 -0.2174 0.03440 0.02477 -0.0222 0.8763 0.7175
-3.250 -0.1889 0.03425 0.02445 -0.0224 0.8718 0.7241
-3.000 -0.1635 0.03391 0.02392 -0.0228 0.8674 0.7328
-2.750 -0.1432 0.03377 0.02365 -0.0220 0.8620 0.7394
-2.500 -0.1221 0.03360 0.02336 -0.0214 0.8564 0.7462
-2.250 -0.0993 0.03329 0.02290 -0.0215 0.8516 0.7534
-2.000 -0.0730 0.03317 0.02267 -0.0216 0.8472 0.7585
-1.750 -0.0594 0.03304 0.02246 -0.0202 0.8405 0.7655
-1.500 -0.0341 0.03287 0.02218 -0.0204 0.8357 0.7707
-1.250 -0.0041 0.03273 0.02194 -0.0212 0.8316 0.7753
-1.000 0.0063 0.03273 0.02190 -0.0194 0.8242 0.7816
-0.750 0.0307 0.03260 0.02169 -0.0195 0.8189 0.7863
-0.500 0.0604 0.03251 0.02154 -0.0201 0.8145 0.7902
-0.250 0.0727 0.03261 0.02162 -0.0184 0.8067 0.7951
0.000 0.0974 0.03249 0.02143 -0.0189 0.8011 0.8001
0.250 0.1193 0.03255 0.02147 -0.0184 0.7947 0.8036
0.500 0.1403 0.03262 0.02154 -0.0178 0.7875 0.8072
0.750 0.1716 0.03253 0.02140 -0.0187 0.7824 0.8109
1.000 0.1837 0.03274 0.02162 -0.0173 0.7730 0.8156
1.250 0.2136 0.03268 0.02155 -0.0180 0.7671 0.8188
1.500 0.2301 0.03289 0.02180 -0.0167 0.7580 0.8222
1.750 0.2590 0.03287 0.02178 -0.0171 0.7511 0.8256
2.000 0.2766 0.03308 0.02203 -0.0162 0.7415 0.8297
2.250 0.3066 0.03302 0.02198 -0.0169 0.7342 0.8331
2.500 0.3238 0.03326 0.02229 -0.0158 0.7237 0.8364
3.000 0.3719 0.03341 0.02255 -0.0150 0.7050 0.8434
3.250 0.4028 0.03328 0.02247 -0.0155 0.6972 0.8468
3.500 0.4238 0.03342 0.02269 -0.0150 0.6855 0.8504
3.750 0.4429 0.03356 0.02293 -0.0139 0.6734 0.8539
4.000 0.4778 0.03310 0.02256 -0.0142 0.6656 0.8572
4.500 0.5158 0.03324 0.02290 -0.0123 0.6370 0.8654
4.750 0.5367 0.03312 0.02290 -0.0113 0.6228 0.8691
5.000 0.5586 0.03291 0.02283 -0.0102 0.6083 0.8733
5.250 0.5816 0.03265 0.02269 -0.0093 0.5936 0.8780
5.500 0.6054 0.03235 0.02251 -0.0086 0.5782 0.8827
5.750 0.6281 0.03198 0.02230 -0.0075 0.5625 0.8871
6.000 0.6519 0.03161 0.02206 -0.0066 0.5459 0.8919
6.250 0.6770 0.03119 0.02176 -0.0058 0.5283 0.8974
6.500 0.7034 0.03065 0.02135 -0.0049 0.5101 0.9030
6.750 0.7332 0.02999 0.02075 -0.0042 0.4909 0.9091
7.000 0.7565 0.02986 0.02070 -0.0034 0.4673 0.9162
7.250 0.7845 0.02953 0.02034 -0.0027 0.4438 0.9232
7.500 0.8074 0.02968 0.02047 -0.0020 0.4182 0.9317
7.750 0.8320 0.02988 0.02060 -0.0016 0.3936 0.9416
8.000 0.8522 0.03050 0.02122 -0.0012 0.3685 0.9564
8.250 0.8736 0.03114 0.02179 -0.0012 0.3458 0.9809
8.500 0.8896 0.03191 0.02251 -0.0006 0.3256 1.0000
8.750 0.9066 0.03293 0.02353 -0.0004 0.3061 1.0000
9.000 0.9241 0.03402 0.02460 -0.0004 0.2881 1.0000
9.250 0.9417 0.03518 0.02574 -0.0004 0.2714 1.0000
9.500 0.9589 0.03639 0.02697 -0.0004 0.2560 1.0000
9.750 0.9760 0.03765 0.02824 -0.0004 0.2417 1.0000
10.000 0.9924 0.03895 0.02953 -0.0003 0.2283 1.0000
10.250 1.0092 0.04024 0.03078 -0.0002 0.2157 1.0000
10.500 1.0219 0.04183 0.03249 0.0000 0.2032 1.0000
10.750 1.0348 0.04345 0.03422 0.0002 0.1918 1.0000
11.000 1.0486 0.04499 0.03577 0.0004 0.1815 1.0000
11.250 1.0603 0.04666 0.03749 0.0007 0.1715 1.0000
11.500 1.0698 0.04867 0.03966 0.0010 0.1623 1.0000
11.750 1.0832 0.05021 0.04114 0.0013 0.1541 1.0000
12.000 1.0872 0.05272 0.04393 0.0015 0.1463 1.0000
12.250 1.0998 0.05437 0.04551 0.0019 0.1394 1.0000
12.500 1.0994 0.05735 0.04881 0.0020 0.1329 1.0000
12.750 1.1088 0.05928 0.05074 0.0023 0.1271 1.0000
13.000 1.1076 0.06249 0.05418 0.0023 0.1221 1.0000
13.250 1.1048 0.06581 0.05772 0.0022 0.1174 1.0000
13.500 1.1158 0.06752 0.05938 0.0024 0.1127 1.0000
13.750 1.1029 0.07222 0.06440 0.0017 0.1097 1.0000
14.000 1.0867 0.07745 0.06992 0.0006 0.1069 1.0000
14.250 1.0723 0.08259 0.07528 -0.0009 0.1043 1.0000
14.500 1.0741 0.08554 0.07826 -0.0014 0.1010 1.0000
14.750 1.0651 0.09022 0.08304 -0.0028 0.0987 1.0000
15.000 1.0242 0.10032 0.09344 -0.0077 0.0982 1.0000
15.250 0.9622 0.11629 0.10963 -0.0167 0.0983 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AS5046 (16%) (as5046-il)