AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5046 (16%) (as5046-il) Reynolds number: 500,000 Max Cl/Cd: 77.7 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5046-il-500000.txt Download as CSV file: xf-as5046-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.3638 0.14905 0.14686 -0.0203 1.0000 0.0190
-15.500 -0.3635 0.14624 0.14406 -0.0216 1.0000 0.0196
-15.250 -0.5521 0.16094 0.15849 -0.0057 1.0000 0.0178
-12.750 -0.4559 0.08608 0.08334 -0.0541 0.8196 0.0237
-12.500 -0.5002 0.07479 0.07191 -0.0600 0.8176 0.0230
-12.250 -0.5428 0.06570 0.06264 -0.0638 0.8142 0.0225
-12.000 -0.5746 0.05908 0.05585 -0.0657 0.8096 0.0224
-11.750 -0.6013 0.05366 0.05026 -0.0665 0.8047 0.0224
-11.500 -0.6239 0.04911 0.04552 -0.0667 0.8001 0.0224
-11.250 -0.6420 0.04530 0.04156 -0.0664 0.7960 0.0225
-11.000 -0.6580 0.04190 0.03801 -0.0658 0.7918 0.0226
-10.750 -0.6712 0.03899 0.03493 -0.0648 0.7876 0.0229
-10.500 -0.6825 0.03640 0.03214 -0.0635 0.7837 0.0234
-9.500 -0.7440 0.03188 0.02552 -0.0521 0.7761 0.0176
-9.250 -0.7169 0.02951 0.02318 -0.0521 0.7735 0.0162
-9.000 -0.6954 0.02731 0.02076 -0.0515 0.7710 0.0157
-8.750 -0.6724 0.02555 0.01879 -0.0510 0.7685 0.0156
-8.500 -0.6474 0.02370 0.01672 -0.0504 0.7661 0.0151
-8.250 -0.6227 0.02224 0.01510 -0.0497 0.7638 0.0148
-8.000 -0.5991 0.02120 0.01402 -0.0492 0.7615 0.0149
-7.750 -0.5764 0.02030 0.01308 -0.0486 0.7593 0.0151
-7.500 -0.5543 0.01948 0.01224 -0.0481 0.7571 0.0154
-7.250 -0.5325 0.01871 0.01143 -0.0475 0.7550 0.0158
-7.000 -0.5106 0.01800 0.01067 -0.0470 0.7530 0.0162
-6.750 -0.4883 0.01734 0.00995 -0.0466 0.7510 0.0167
-6.500 -0.4649 0.01683 0.00937 -0.0463 0.7488 0.0172
-6.250 -0.4445 0.01588 0.00841 -0.0459 0.7469 0.0180
-6.000 -0.4206 0.01529 0.00783 -0.0458 0.7450 0.0189
-5.750 -0.3953 0.01484 0.00735 -0.0458 0.7431 0.0203
-5.500 -0.3706 0.01426 0.00676 -0.0458 0.7412 0.0223
-5.250 -0.3443 0.01386 0.00633 -0.0459 0.7393 0.0249
-5.000 -0.3183 0.01337 0.00582 -0.0460 0.7373 0.0297
-4.750 -0.2936 0.01255 0.00519 -0.0461 0.7353 0.0693
-4.500 -0.2757 0.00987 0.00396 -0.0473 0.7334 0.3932
-4.250 -0.2489 0.00911 0.00391 -0.0480 0.7317 0.5618
-4.000 -0.2192 0.00928 0.00412 -0.0482 0.7299 0.5978
-3.750 -0.1895 0.00953 0.00435 -0.0484 0.7277 0.6163
-3.500 -0.1602 0.00988 0.00471 -0.0484 0.7256 0.6298
-3.250 -0.1310 0.01020 0.00501 -0.0484 0.7233 0.6403
-3.000 -0.1018 0.01045 0.00524 -0.0484 0.7211 0.6469
-2.750 -0.0715 0.01061 0.00528 -0.0489 0.7189 0.6526
-2.500 -0.0427 0.01068 0.00534 -0.0490 0.7168 0.6558
-2.250 -0.0136 0.01081 0.00546 -0.0492 0.7146 0.6589
-2.000 0.0158 0.01085 0.00550 -0.0495 0.7120 0.6622
-1.750 0.0454 0.01087 0.00549 -0.0499 0.7091 0.6657
-1.500 0.0754 0.01089 0.00545 -0.0505 0.7060 0.6688
-1.250 0.1047 0.01083 0.00535 -0.0508 0.7029 0.6711
-1.000 0.1339 0.01086 0.00535 -0.0510 0.6998 0.6731
-0.750 0.1629 0.01086 0.00536 -0.0513 0.6964 0.6751
-0.500 0.1921 0.01084 0.00535 -0.0515 0.6926 0.6775
-0.250 0.2216 0.01083 0.00532 -0.0519 0.6891 0.6802
0.000 0.2514 0.01083 0.00527 -0.0523 0.6859 0.6828
0.250 0.2815 0.01086 0.00524 -0.0529 0.6829 0.6848
0.500 0.3111 0.01081 0.00519 -0.0534 0.6792 0.6865
0.750 0.3400 0.01068 0.00510 -0.0536 0.6746 0.6881
1.000 0.3691 0.01056 0.00497 -0.0538 0.6694 0.6896
1.250 0.3983 0.01051 0.00489 -0.0541 0.6643 0.6910
1.500 0.4272 0.01040 0.00483 -0.0543 0.6584 0.6927
1.750 0.4565 0.01032 0.00475 -0.0546 0.6533 0.6944
2.000 0.4861 0.01028 0.00467 -0.0550 0.6487 0.6962
2.250 0.5152 0.01019 0.00464 -0.0553 0.6425 0.6978
2.500 0.5446 0.01011 0.00456 -0.0557 0.6367 0.6995
2.750 0.5740 0.01005 0.00450 -0.0560 0.6305 0.7012
3.000 0.6033 0.00998 0.00446 -0.0563 0.6218 0.7027
3.250 0.6320 0.00985 0.00435 -0.0565 0.6139 0.7041
3.500 0.6605 0.00976 0.00430 -0.0567 0.6031 0.7054
3.750 0.6889 0.00970 0.00427 -0.0568 0.5894 0.7068
4.000 0.7168 0.00969 0.00424 -0.0568 0.5725 0.7083
4.250 0.7440 0.00974 0.00426 -0.0568 0.5493 0.7100
4.500 0.7698 0.00991 0.00430 -0.0565 0.5160 0.7117
4.750 0.7941 0.01022 0.00444 -0.0559 0.4763 0.7134
5.000 0.8183 0.01059 0.00465 -0.0555 0.4388 0.7150
5.250 0.8426 0.01097 0.00489 -0.0551 0.4050 0.7165
5.500 0.8666 0.01139 0.00516 -0.0547 0.3720 0.7180
5.750 0.8904 0.01179 0.00543 -0.0542 0.3415 0.7196
6.000 0.9137 0.01218 0.00571 -0.0537 0.3127 0.7213
6.250 0.9369 0.01258 0.00602 -0.0531 0.2841 0.7228
6.500 0.9599 0.01301 0.00636 -0.0526 0.2592 0.7244
6.750 0.9832 0.01341 0.00669 -0.0521 0.2380 0.7260
7.000 1.0062 0.01383 0.00703 -0.0515 0.2198 0.7277
7.250 1.0294 0.01423 0.00739 -0.0510 0.2044 0.7294
7.500 1.0526 0.01462 0.00775 -0.0505 0.1914 0.7314
7.750 1.0755 0.01504 0.00813 -0.0500 0.1796 0.7333
8.000 1.0976 0.01550 0.00854 -0.0493 0.1686 0.7351
8.250 1.1201 0.01584 0.00891 -0.0487 0.1584 0.7369
8.500 1.1420 0.01622 0.00931 -0.0480 0.1488 0.7387
8.750 1.1623 0.01671 0.00977 -0.0471 0.1390 0.7406
9.000 1.1833 0.01713 0.01021 -0.0463 0.1294 0.7425
9.250 1.2034 0.01759 0.01068 -0.0454 0.1202 0.7446
9.500 1.2214 0.01816 0.01122 -0.0442 0.1108 0.7468
9.750 1.2388 0.01872 0.01177 -0.0429 0.1018 0.7490
10.000 1.2527 0.01928 0.01235 -0.0410 0.0944 0.7512
10.250 1.2649 0.02001 0.01307 -0.0390 0.0869 0.7538
10.500 1.2802 0.02067 0.01378 -0.0376 0.0806 0.7564
10.750 1.2921 0.02159 0.01471 -0.0359 0.0747 0.7589
11.000 1.3058 0.02243 0.01560 -0.0346 0.0699 0.7617
11.250 1.3144 0.02369 0.01687 -0.0331 0.0652 0.7645
11.500 1.3293 0.02460 0.01786 -0.0323 0.0617 0.7673
11.750 1.3400 0.02587 0.01916 -0.0314 0.0582 0.7703
12.000 1.3485 0.02738 0.02075 -0.0305 0.0551 0.7735
12.250 1.3617 0.02856 0.02203 -0.0299 0.0526 0.7771
12.500 1.3717 0.03003 0.02354 -0.0293 0.0500 0.7809
12.750 1.3747 0.03212 0.02566 -0.0284 0.0475 0.7847
13.000 1.3869 0.03339 0.02708 -0.0279 0.0458 0.7891
13.250 1.3963 0.03492 0.02871 -0.0273 0.0440 0.7945
13.500 1.4026 0.03674 0.03059 -0.0267 0.0423 0.8005
13.750 1.4015 0.03920 0.03313 -0.0257 0.0405 0.8074
14.000 1.4082 0.04099 0.03506 -0.0252 0.0393 0.8163
14.250 1.4146 0.04279 0.03704 -0.0246 0.0380 0.8287
14.500 1.4189 0.04473 0.03914 -0.0240 0.0368 0.8506
14.750 1.4093 0.04626 0.04095 -0.0205 0.0361 1.0000
15.000 1.4085 0.04897 0.04369 -0.0202 0.0350 1.0000
15.250 1.4009 0.05242 0.04720 -0.0199 0.0339 1.0000
15.500 1.4064 0.05472 0.04961 -0.0200 0.0331 1.0000
15.750 1.4093 0.05733 0.05232 -0.0201 0.0322 1.0000
16.000 1.4106 0.06022 0.05530 -0.0204 0.0313 1.0000
16.250 1.4107 0.06332 0.05848 -0.0209 0.0305 1.0000
16.500 1.4088 0.06676 0.06199 -0.0216 0.0297 1.0000
16.750 1.4028 0.07074 0.06604 -0.0223 0.0290 1.0000
17.000 1.3929 0.07520 0.07056 -0.0231 0.0283 1.0000
17.250 1.3922 0.07882 0.07432 -0.0242 0.0278 1.0000
17.500 1.3896 0.08272 0.07834 -0.0254 0.0272 1.0000
17.750 1.3849 0.08692 0.08266 -0.0267 0.0266 1.0000
18.000 1.3797 0.09128 0.08712 -0.0283 0.0261 1.0000
18.250 1.3736 0.09582 0.09175 -0.0299 0.0256 1.0000
18.500 1.3669 0.10052 0.09654 -0.0318 0.0251 1.0000
18.750 1.3593 0.10537 0.10147 -0.0337 0.0247 1.0000
19.000 1.3507 0.11030 0.10646 -0.0357 0.0242 1.0000
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Polar data table (+)
Polar graphs
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