RAE 102 AIRFOIL (rae102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 102 AIRFOIL (rae102-il) Reynolds number: 1,000,000 Max Cl/Cd: 65.59 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae102-il-1000000.txt Download as CSV file: xf-rae102-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 102 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9800 0.06146 0.05923 -0.0266 1.0000 0.0067
-13.500 -0.9898 0.05627 0.05394 -0.0301 1.0000 0.0068
-13.250 -1.0238 0.04798 0.04533 -0.0345 1.0000 0.0066
-13.000 -1.0398 0.04326 0.04043 -0.0362 1.0000 0.0066
-12.750 -1.0535 0.03942 0.03641 -0.0365 1.0000 0.0067
-12.500 -1.0592 0.03694 0.03381 -0.0358 1.0000 0.0068
-12.250 -1.0655 0.03463 0.03137 -0.0342 1.0000 0.0069
-12.000 -1.0650 0.03321 0.02986 -0.0323 1.0000 0.0070
-11.750 -1.0788 0.03046 0.02684 -0.0281 1.0000 0.0069
-11.500 -1.0757 0.02929 0.02557 -0.0252 1.0000 0.0071
-11.250 -1.0649 0.02835 0.02455 -0.0234 1.0000 0.0072
-11.000 -1.0575 0.02670 0.02272 -0.0212 1.0000 0.0073
-10.750 -1.0449 0.02554 0.02144 -0.0195 1.0000 0.0075
-10.500 -1.0334 0.02400 0.01972 -0.0176 1.0000 0.0077
-10.250 -1.0189 0.02277 0.01834 -0.0160 1.0000 0.0078
-10.000 -1.0036 0.02154 0.01696 -0.0144 1.0000 0.0080
-9.750 -0.9867 0.02049 0.01578 -0.0129 1.0000 0.0082
-9.500 -0.9686 0.01958 0.01475 -0.0116 1.0000 0.0086
-9.250 -0.9501 0.01868 0.01374 -0.0102 1.0000 0.0088
-9.000 -0.9284 0.01829 0.01329 -0.0093 1.0000 0.0091
-8.750 -0.9144 0.01672 0.01154 -0.0072 1.0000 0.0095
-8.500 -0.8992 0.01547 0.01018 -0.0053 1.0000 0.0100
-8.250 -0.8793 0.01486 0.00952 -0.0040 1.0000 0.0105
-8.000 -0.8586 0.01435 0.00897 -0.0028 1.0000 0.0109
-7.750 -0.8380 0.01382 0.00840 -0.0016 1.0000 0.0114
-7.500 -0.8171 0.01334 0.00787 -0.0004 1.0000 0.0121
-7.250 -0.7959 0.01293 0.00741 0.0008 1.0000 0.0126
-7.000 -0.7743 0.01257 0.00700 0.0020 1.0000 0.0129
-6.750 -0.7584 0.01162 0.00595 0.0041 1.0000 0.0143
-6.500 -0.7375 0.01125 0.00557 0.0054 1.0000 0.0154
-6.250 -0.7163 0.01095 0.00527 0.0066 1.0000 0.0166
-6.000 -0.6949 0.01071 0.00501 0.0078 1.0000 0.0177
-5.750 -0.6666 0.01016 0.00438 0.0075 0.9987 0.0200
-5.500 -0.6319 0.00980 0.00404 0.0058 0.9963 0.0230
-5.250 -0.5969 0.00953 0.00375 0.0041 0.9936 0.0255
-5.000 -0.5644 0.00912 0.00337 0.0029 0.9897 0.0324
-4.750 -0.5300 0.00878 0.00305 0.0013 0.9859 0.0415
-4.500 -0.4949 0.00845 0.00278 -0.0005 0.9828 0.0563
-4.250 -0.4638 0.00806 0.00252 -0.0014 0.9759 0.0834
-4.000 -0.4291 0.00760 0.00225 -0.0032 0.9706 0.1285
-3.750 -0.3986 0.00705 0.00198 -0.0041 0.9605 0.1974
-3.500 -0.3684 0.00642 0.00171 -0.0050 0.9478 0.2904
-3.250 -0.3421 0.00576 0.00146 -0.0051 0.9301 0.4043
-3.000 -0.3160 0.00549 0.00133 -0.0047 0.9099 0.4671
-2.750 -0.2902 0.00536 0.00124 -0.0042 0.8885 0.5028
-2.500 -0.2644 0.00529 0.00117 -0.0037 0.8682 0.5280
-2.250 -0.2383 0.00525 0.00111 -0.0032 0.8483 0.5492
-2.000 -0.2123 0.00521 0.00105 -0.0028 0.8294 0.5683
-1.750 -0.1861 0.00519 0.00100 -0.0023 0.8114 0.5867
-1.500 -0.1597 0.00517 0.00096 -0.0019 0.7943 0.6041
-1.250 -0.1331 0.00516 0.00093 -0.0016 0.7780 0.6208
-1.000 -0.1065 0.00514 0.00091 -0.0013 0.7628 0.6371
-0.750 -0.0799 0.00512 0.00089 -0.0010 0.7479 0.6532
-0.500 -0.0532 0.00511 0.00088 -0.0006 0.7327 0.6693
-0.250 -0.0266 0.00510 0.00087 -0.0003 0.7172 0.6854
0.000 0.0000 0.00510 0.00087 0.0000 0.7014 0.7015
0.250 0.0266 0.00510 0.00087 0.0003 0.6854 0.7172
0.500 0.0533 0.00511 0.00088 0.0006 0.6693 0.7327
0.750 0.0799 0.00512 0.00089 0.0010 0.6532 0.7479
1.000 0.1065 0.00514 0.00091 0.0013 0.6371 0.7629
1.250 0.1331 0.00516 0.00093 0.0016 0.6207 0.7780
1.500 0.1597 0.00517 0.00096 0.0019 0.6039 0.7942
1.750 0.1861 0.00519 0.00100 0.0023 0.5865 0.8114
2.000 0.2123 0.00521 0.00105 0.0028 0.5689 0.8294
2.250 0.2383 0.00525 0.00111 0.0032 0.5498 0.8483
2.500 0.2644 0.00529 0.00117 0.0037 0.5276 0.8682
2.750 0.2903 0.00536 0.00124 0.0042 0.5026 0.8885
3.000 0.3160 0.00549 0.00133 0.0047 0.4665 0.9099
3.250 0.3423 0.00575 0.00146 0.0050 0.4066 0.9300
3.500 0.3686 0.00641 0.00170 0.0050 0.2920 0.9479
3.750 0.3986 0.00705 0.00198 0.0041 0.1971 0.9606
4.000 0.4293 0.00759 0.00225 0.0032 0.1287 0.9707
4.250 0.4639 0.00806 0.00252 0.0014 0.0836 0.9761
4.500 0.4947 0.00845 0.00278 0.0005 0.0560 0.9831
4.750 0.5304 0.00878 0.00305 -0.0014 0.0415 0.9861
5.000 0.5646 0.00912 0.00337 -0.0029 0.0324 0.9898
5.250 0.5971 0.00953 0.00375 -0.0041 0.0256 0.9937
5.500 0.6322 0.00980 0.00404 -0.0059 0.0229 0.9964
5.750 0.6670 0.01017 0.00440 -0.0076 0.0198 0.9989
6.000 0.6942 0.01070 0.00499 -0.0077 0.0177 1.0000
6.250 0.7155 0.01096 0.00528 -0.0064 0.0167 1.0000
6.500 0.7368 0.01125 0.00557 -0.0052 0.0154 1.0000
6.750 0.7576 0.01162 0.00595 -0.0040 0.0142 1.0000
7.000 0.7737 0.01258 0.00701 -0.0018 0.0129 1.0000
7.250 0.7955 0.01291 0.00739 -0.0007 0.0126 1.0000
7.500 0.8168 0.01333 0.00786 0.0004 0.0120 1.0000
7.750 0.8376 0.01383 0.00841 0.0017 0.0114 1.0000
8.000 0.8583 0.01435 0.00898 0.0029 0.0110 1.0000
8.250 0.8791 0.01487 0.00953 0.0040 0.0105 1.0000
8.500 0.8991 0.01548 0.01019 0.0053 0.0101 1.0000
8.750 0.9144 0.01674 0.01156 0.0072 0.0095 1.0000
9.000 0.9291 0.01823 0.01322 0.0092 0.0091 1.0000
9.250 0.9496 0.01884 0.01392 0.0103 0.0089 1.0000
9.500 0.9698 0.01946 0.01462 0.0114 0.0085 1.0000
9.750 0.9869 0.02055 0.01585 0.0129 0.0083 1.0000
10.000 1.0040 0.02160 0.01702 0.0143 0.0081 1.0000
10.250 1.0198 0.02277 0.01833 0.0158 0.0079 1.0000
10.500 1.0339 0.02409 0.01981 0.0175 0.0077 1.0000
10.750 1.0474 0.02532 0.02119 0.0191 0.0075 1.0000
11.000 1.0569 0.02695 0.02300 0.0212 0.0074 1.0000
11.250 1.0703 0.02780 0.02393 0.0227 0.0072 1.0000
11.500 1.0744 0.02963 0.02595 0.0252 0.0071 1.0000
11.750 1.0748 0.03105 0.02750 0.0284 0.0070 1.0000
12.000 1.0708 0.03280 0.02940 0.0316 0.0070 1.0000
12.250 1.0713 0.03423 0.03092 0.0337 0.0068 1.0000
12.500 1.0644 0.03659 0.03343 0.0354 0.0068 1.0000
12.750 1.0571 0.03927 0.03626 0.0362 0.0067 1.0000
13.000 1.0400 0.04352 0.04071 0.0358 0.0067 1.0000
13.250 1.0176 0.04926 0.04671 0.0337 0.0068 1.0000
13.500 1.0039 0.05438 0.05196 0.0307 0.0067 1.0000
13.750 0.9863 0.06079 0.05851 0.0265 0.0066 1.0000
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Polar data table (+)
Polar graphs
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