AS5048 (18%) (as5048-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5048 (18%) (as5048-il) Reynolds number: 100,000 Max Cl/Cd: 41.21 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5048-il-100000.txt Download as CSV file: xf-as5048-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AS5048 (18%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4325 0.09082 0.08631 -0.0592 1.0000 0.0954
-11.750 -0.4982 0.07878 0.07420 -0.0648 1.0000 0.0939
-11.500 -0.5512 0.07098 0.06630 -0.0666 1.0000 0.0934
-11.250 -0.6055 0.06488 0.06006 -0.0662 1.0000 0.0923
-11.000 -0.6622 0.06079 0.05580 -0.0632 1.0000 0.0910
-10.750 -0.7059 0.05914 0.05413 -0.0577 1.0000 0.0906
-10.500 -0.7229 0.06001 0.05525 -0.0513 1.0000 0.0918
-10.250 -0.8069 0.06412 0.05869 -0.0467 1.0000 0.0925
-10.000 -0.8731 0.06739 0.06141 -0.0360 0.9953 0.0887
-9.750 -0.8631 0.05696 0.05008 -0.0356 0.9894 0.0645
-9.500 -0.8405 0.05227 0.04517 -0.0372 0.9845 0.0628
-9.250 -0.8205 0.04839 0.04091 -0.0378 0.9780 0.0608
-9.000 -0.8035 0.04466 0.03640 -0.0372 0.9711 0.0571
-8.750 -0.7772 0.04313 0.03428 -0.0374 0.9652 0.0555
-8.500 -0.7461 0.04024 0.03118 -0.0384 0.9613 0.0552
-8.250 -0.7153 0.03807 0.02878 -0.0392 0.9570 0.0552
-8.000 -0.6748 0.03554 0.02621 -0.0413 0.9549 0.0566
-7.750 -0.6343 0.03376 0.02451 -0.0438 0.9529 0.0599
-7.500 -0.5950 0.03238 0.02309 -0.0455 0.9503 0.0626
-7.250 -0.5634 0.03134 0.02201 -0.0459 0.9459 0.0648
-7.000 -0.5334 0.02991 0.02079 -0.0467 0.9425 0.0690
-6.750 -0.5060 0.02884 0.01970 -0.0475 0.9392 0.0754
-6.500 -0.4981 0.02791 0.01881 -0.0452 0.9333 0.0802
-6.250 -0.4826 0.02701 0.01786 -0.0440 0.9280 0.0885
-6.000 -0.4652 0.02541 0.01652 -0.0437 0.9242 0.1155
-5.750 -0.4825 0.02374 0.01575 -0.0379 0.9170 0.2278
-5.500 -0.4914 0.02376 0.01785 -0.0299 0.9119 0.5783
-5.250 -0.4534 0.02745 0.02140 -0.0271 0.9091 0.6395
-5.000 -0.3999 0.03154 0.02539 -0.0253 0.9079 0.6715
-4.750 -0.2805 0.03761 0.03125 -0.0292 0.9112 0.6955
-4.500 -0.2426 0.03738 0.03083 -0.0312 0.9090 0.7079
-4.250 -0.2686 0.03730 0.03074 -0.0234 0.9010 0.7219
-4.000 -0.1801 0.03762 0.03081 -0.0321 0.9022 0.7279
-3.750 -0.1797 0.03733 0.03046 -0.0285 0.8963 0.7402
-3.500 -0.1174 0.03723 0.03019 -0.0342 0.8954 0.7477
-3.250 -0.0888 0.03671 0.02955 -0.0353 0.8923 0.7579
-3.000 -0.0278 0.03628 0.02897 -0.0414 0.8912 0.7655
-2.750 -0.0896 0.03688 0.02966 -0.0270 0.8804 0.7751
-2.500 -0.0345 0.03655 0.02919 -0.0322 0.8784 0.7819
-2.250 -0.0233 0.03601 0.02858 -0.0307 0.8745 0.7906
-2.000 -0.0442 0.03668 0.02928 -0.0227 0.8664 0.7965
-1.750 -0.0882 0.03630 0.02890 -0.0123 0.8587 0.8063
-1.500 -0.0052 0.03602 0.02849 -0.0220 0.8580 0.8095
-1.250 -0.0860 0.03665 0.02921 -0.0046 0.8465 0.8172
-1.000 -0.0781 0.03608 0.02857 -0.0027 0.8415 0.8238
-0.750 -0.0047 0.03585 0.02825 -0.0107 0.8397 0.8265
-0.500 -0.0647 0.03634 0.02879 0.0028 0.8287 0.8333
-0.250 -0.0397 0.03590 0.02827 0.0020 0.8238 0.8384
0.000 -0.0368 0.03599 0.02835 0.0052 0.8166 0.8426
0.250 -0.0205 0.03606 0.02840 0.0063 0.8094 0.8463
0.500 0.0300 0.03579 0.02808 0.0021 0.8054 0.8494
0.750 0.0081 0.03600 0.02828 0.0084 0.7947 0.8547
1.000 0.0460 0.03570 0.02793 0.0060 0.7891 0.8577
1.250 0.1077 0.03538 0.02758 0.0006 0.7860 0.8595
1.500 0.0888 0.03594 0.02817 0.0067 0.7732 0.8633
1.750 0.1486 0.03549 0.02771 0.0016 0.7698 0.8653
2.000 0.1337 0.03606 0.02829 0.0068 0.7565 0.8701
2.250 0.1901 0.03549 0.02771 0.0023 0.7529 0.8720
2.500 0.1849 0.03606 0.02830 0.0059 0.7395 0.8755
2.750 0.2427 0.03544 0.02770 0.0018 0.7360 0.8774
3.000 0.2411 0.03606 0.02835 0.0053 0.7222 0.8812
3.250 0.3025 0.03528 0.02759 0.0007 0.7190 0.8828
3.500 0.3020 0.03578 0.02813 0.0039 0.7048 0.8866
3.750 0.3657 0.03481 0.02719 -0.0009 0.7018 0.8886
4.000 0.3689 0.03515 0.02757 0.0021 0.6875 0.8925
4.250 0.4365 0.03376 0.02623 -0.0026 0.6844 0.8939
4.500 0.4476 0.03387 0.02641 -0.0004 0.6702 0.8971
4.750 0.4779 0.03337 0.02597 -0.0004 0.6601 0.9002
5.000 0.5226 0.03227 0.02493 -0.0021 0.6527 0.9032
5.250 0.5770 0.03084 0.02354 -0.0051 0.6480 0.9059
5.500 0.5970 0.03044 0.02324 -0.0038 0.6353 0.9095
5.750 0.6188 0.03005 0.02294 -0.0026 0.6228 0.9129
6.000 0.6767 0.02831 0.02127 -0.0060 0.6173 0.9150
6.250 0.6955 0.02778 0.02084 -0.0043 0.6036 0.9198
6.500 0.7209 0.02697 0.02013 -0.0035 0.5906 0.9246
6.750 0.7582 0.02585 0.01911 -0.0041 0.5777 0.9283
7.000 0.7941 0.02473 0.01806 -0.0047 0.5625 0.9326
7.250 0.8244 0.02377 0.01713 -0.0044 0.5439 0.9377
7.500 0.8663 0.02272 0.01603 -0.0059 0.5209 0.9413
7.750 0.8912 0.02242 0.01567 -0.0052 0.4915 0.9471
8.000 0.9154 0.02240 0.01551 -0.0046 0.4595 0.9539
8.250 0.9366 0.02273 0.01566 -0.0038 0.4272 0.9622
8.500 0.9584 0.02331 0.01605 -0.0035 0.3961 0.9707
8.750 0.9821 0.02405 0.01661 -0.0038 0.3678 0.9794
9.000 1.0065 0.02489 0.01734 -0.0046 0.3419 0.9887
9.250 1.0343 0.02582 0.01814 -0.0061 0.3185 0.9973
9.500 1.0343 0.02617 0.01839 -0.0025 0.3055 1.0000
9.750 1.0415 0.02684 0.01904 -0.0006 0.2906 1.0000
10.000 1.0568 0.02774 0.01990 0.0000 0.2750 1.0000
10.250 1.0727 0.02874 0.02086 0.0004 0.2602 1.0000
10.500 1.0886 0.02981 0.02190 0.0009 0.2463 1.0000
10.750 1.1045 0.03093 0.02300 0.0014 0.2331 1.0000
11.000 1.1219 0.03208 0.02405 0.0017 0.2207 1.0000
11.250 1.1388 0.03322 0.02510 0.0022 0.2085 1.0000
11.500 1.1464 0.03455 0.02656 0.0037 0.1977 1.0000
11.750 1.1606 0.03591 0.02790 0.0044 0.1872 1.0000
12.000 1.1817 0.03716 0.02897 0.0044 0.1762 1.0000
12.250 1.1823 0.03874 0.03081 0.0064 0.1680 1.0000
12.500 1.2000 0.04016 0.03214 0.0068 0.1590 1.0000
12.750 1.2038 0.04179 0.03392 0.0083 0.1515 1.0000
13.000 1.2202 0.04335 0.03543 0.0088 0.1439 1.0000
13.250 1.2218 0.04521 0.03750 0.0103 0.1377 1.0000
13.500 1.2427 0.04667 0.03881 0.0104 0.1306 1.0000
13.750 1.2369 0.04897 0.04143 0.0121 0.1262 1.0000
14.000 1.2458 0.05063 0.04313 0.0129 0.1210 1.0000
14.250 1.2571 0.05270 0.04522 0.0135 0.1161 1.0000
14.500 1.2488 0.05546 0.04828 0.0149 0.1127 1.0000
14.750 1.2488 0.05778 0.05074 0.0158 0.1090 1.0000
15.000 1.2722 0.05935 0.05216 0.0158 0.1042 1.0000
15.250 1.2533 0.06297 0.05615 0.0171 0.1025 1.0000
15.500 1.2363 0.06680 0.06028 0.0179 0.1006 1.0000
15.750 1.2224 0.07060 0.06432 0.0183 0.0985 1.0000
16.000 1.2113 0.07430 0.06820 0.0185 0.0965 1.0000
16.250 1.2424 0.07513 0.06879 0.0187 0.0922 1.0000
16.500 1.2119 0.08050 0.07449 0.0185 0.0917 1.0000
16.750 1.1781 0.08680 0.08110 0.0174 0.0915 1.0000
17.000 1.1406 0.09424 0.08882 0.0152 0.0915 1.0000
17.250 1.0971 0.10343 0.09828 0.0115 0.0918 1.0000
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Polar data table (+)
Polar graphs
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