RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 27 AIRFOIL (raf27-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.4 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf27-il-1000000.txt Download as CSV file: xf-raf27-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 27 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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9536 0.09287 0.09088 -0.0094 1.0000 0.0072
-15.000 -1.0206 0.07466 0.07240 -0.0204 1.0000 0.0069
-14.750 -1.0368 0.06719 0.06482 -0.0254 1.0000 0.0070
-14.500 -1.0639 0.05821 0.05565 -0.0315 1.0000 0.0070
-14.250 -1.0854 0.05105 0.04829 -0.0361 1.0000 0.0069
-14.000 -1.0982 0.04594 0.04302 -0.0390 1.0000 0.0070
-13.750 -1.1163 0.04079 0.03765 -0.0408 1.0000 0.0069
-13.500 -1.1188 0.03804 0.03477 -0.0412 1.0000 0.0071
-13.250 -1.1232 0.03539 0.03197 -0.0407 1.0000 0.0072
-13.000 -1.1310 0.03272 0.02912 -0.0392 1.0000 0.0072
-12.750 -1.1290 0.03119 0.02747 -0.0375 1.0000 0.0073
-12.500 -1.1334 0.02923 0.02533 -0.0346 1.0000 0.0074
-12.250 -1.1290 0.02814 0.02414 -0.0320 1.0000 0.0076
-12.000 -1.1295 0.02678 0.02263 -0.0283 1.0000 0.0077
-11.750 -1.1253 0.02546 0.02117 -0.0252 1.0000 0.0078
-11.500 -1.1134 0.02459 0.02018 -0.0231 1.0000 0.0079
-11.250 -1.0989 0.02388 0.01938 -0.0213 1.0000 0.0081
-11.000 -1.0932 0.02215 0.01745 -0.0183 1.0000 0.0083
-10.750 -1.0881 0.02033 0.01545 -0.0151 1.0000 0.0087
-10.500 -1.0730 0.01952 0.01456 -0.0133 1.0000 0.0090
-10.250 -1.0549 0.01898 0.01398 -0.0118 1.0000 0.0094
-10.000 -1.0383 0.01825 0.01317 -0.0101 1.0000 0.0096
-9.750 -1.0190 0.01778 0.01265 -0.0087 1.0000 0.0101
-9.500 -1.0005 0.01722 0.01202 -0.0072 1.0000 0.0105
-9.250 -0.9815 0.01670 0.01143 -0.0057 1.0000 0.0109
-9.000 -0.9633 0.01608 0.01073 -0.0040 1.0000 0.0111
-8.750 -0.9478 0.01520 0.00974 -0.0019 1.0000 0.0115
-8.500 -0.9324 0.01432 0.00881 0.0003 1.0000 0.0124
-8.250 -0.9126 0.01389 0.00834 0.0017 1.0000 0.0130
-8.000 -0.8921 0.01352 0.00794 0.0030 1.0000 0.0137
-7.750 -0.8719 0.01313 0.00752 0.0045 1.0000 0.0144
-7.500 -0.8508 0.01284 0.00717 0.0058 1.0000 0.0150
-7.250 -0.8335 0.01217 0.00645 0.0077 1.0000 0.0164
-7.000 -0.8130 0.01183 0.00611 0.0091 1.0000 0.0176
-6.750 -0.7919 0.01157 0.00583 0.0104 1.0000 0.0189
-6.500 -0.7705 0.01135 0.00560 0.0117 1.0000 0.0199
-6.250 -0.7521 0.01084 0.00502 0.0135 1.0000 0.0220
-6.000 -0.7317 0.01056 0.00476 0.0149 1.0000 0.0241
-5.750 -0.6996 0.01036 0.00454 0.0138 0.9988 0.0262
-5.500 -0.6635 0.00996 0.00411 0.0118 0.9966 0.0297
-5.250 -0.6265 0.00965 0.00380 0.0097 0.9946 0.0332
-5.000 -0.5926 0.00943 0.00356 0.0083 0.9922 0.0356
-4.750 -0.5602 0.00906 0.00322 0.0072 0.9894 0.0429
-4.500 -0.5267 0.00870 0.00295 0.0058 0.9868 0.0597
-4.250 -0.4928 0.00828 0.00269 0.0042 0.9846 0.0923
-4.000 -0.4608 0.00776 0.00241 0.0030 0.9819 0.1448
-3.750 -0.4322 0.00728 0.00219 0.0026 0.9768 0.2051
-3.500 -0.3993 0.00689 0.00199 0.0013 0.9734 0.2534
-3.250 -0.3646 0.00655 0.00182 -0.0003 0.9708 0.2971
-3.000 -0.3355 0.00623 0.00166 -0.0007 0.9640 0.3422
-2.750 -0.3018 0.00590 0.00151 -0.0020 0.9584 0.3922
-2.500 -0.2701 0.00559 0.00139 -0.0030 0.9497 0.4458
-2.250 -0.2361 0.00532 0.00127 -0.0044 0.9388 0.4950
-2.000 -0.2037 0.00513 0.00115 -0.0053 0.9217 0.5292
-1.750 -0.1757 0.00493 0.00106 -0.0052 0.9008 0.5763
-1.500 -0.1501 0.00481 0.00101 -0.0046 0.8794 0.6180
-1.250 -0.1249 0.00477 0.00096 -0.0039 0.8558 0.6467
-1.000 -0.1002 0.00473 0.00093 -0.0030 0.8328 0.6728
-0.750 -0.0757 0.00470 0.00091 -0.0021 0.8111 0.6990
-0.500 -0.0505 0.00470 0.00089 -0.0014 0.7911 0.7193
-0.250 -0.0252 0.00470 0.00088 -0.0007 0.7719 0.7364
0.000 0.0000 0.00470 0.00087 0.0000 0.7533 0.7533
0.250 0.0252 0.00470 0.00088 0.0007 0.7364 0.7721
0.500 0.0505 0.00470 0.00089 0.0014 0.7196 0.7913
0.750 0.0757 0.00470 0.00091 0.0021 0.7001 0.8107
1.000 0.1001 0.00473 0.00093 0.0030 0.6730 0.8328
1.750 0.1755 0.00494 0.00106 0.0053 0.5740 0.9010
2.000 0.2036 0.00514 0.00115 0.0053 0.5282 0.9216
2.250 0.2360 0.00532 0.00127 0.0044 0.4946 0.9387
2.500 0.2702 0.00559 0.00139 0.0030 0.4466 0.9497
2.750 0.3018 0.00590 0.00151 0.0020 0.3929 0.9584
3.000 0.3355 0.00622 0.00166 0.0007 0.3430 0.9640
3.250 0.3645 0.00655 0.00182 0.0003 0.2980 0.9708
3.750 0.4321 0.00728 0.00219 -0.0026 0.2048 0.9767
4.000 0.4610 0.00774 0.00241 -0.0031 0.1473 0.9818
4.250 0.4925 0.00827 0.00269 -0.0042 0.0933 0.9846
4.500 0.5265 0.00871 0.00295 -0.0058 0.0590 0.9867
4.750 0.5601 0.00906 0.00322 -0.0072 0.0428 0.9893
5.000 0.5925 0.00944 0.00357 -0.0083 0.0354 0.9922
5.250 0.6264 0.00965 0.00380 -0.0097 0.0332 0.9945
5.500 0.6632 0.00996 0.00411 -0.0118 0.0297 0.9966
5.750 0.6994 0.01036 0.00454 -0.0137 0.0263 0.9988
6.000 0.7320 0.01056 0.00475 -0.0149 0.0240 1.0000
6.250 0.7523 0.01084 0.00503 -0.0135 0.0220 1.0000
6.500 0.7708 0.01135 0.00559 -0.0117 0.0199 1.0000
6.750 0.7921 0.01157 0.00584 -0.0104 0.0189 1.0000
7.000 0.8131 0.01185 0.00613 -0.0091 0.0177 1.0000
7.250 0.8338 0.01216 0.00644 -0.0078 0.0164 1.0000
7.500 0.8506 0.01288 0.00723 -0.0057 0.0150 1.0000
7.750 0.8719 0.01315 0.00754 -0.0045 0.0144 1.0000
8.000 0.8920 0.01355 0.00798 -0.0030 0.0138 1.0000
8.250 0.9125 0.01392 0.00837 -0.0017 0.0130 1.0000
8.500 0.9327 0.01431 0.00878 -0.0003 0.0123 1.0000
8.750 0.9485 0.01513 0.00967 0.0018 0.0116 1.0000
9.000 0.9627 0.01616 0.01081 0.0041 0.0111 1.0000
9.250 0.9823 0.01661 0.01134 0.0055 0.0108 1.0000
9.500 1.0014 0.01713 0.01193 0.0070 0.0104 1.0000
9.750 1.0195 0.01774 0.01261 0.0087 0.0100 1.0000
10.000 1.0377 0.01831 0.01324 0.0102 0.0097 1.0000
10.250 1.0566 0.01880 0.01377 0.0116 0.0093 1.0000
10.500 1.0742 0.01939 0.01441 0.0131 0.0089 1.0000
10.750 1.0878 0.02036 0.01547 0.0152 0.0086 1.0000
11.000 1.0873 0.02279 0.01815 0.0191 0.0081 1.0000
11.250 1.1005 0.02371 0.01919 0.0211 0.0080 1.0000
11.500 1.1143 0.02448 0.02007 0.0230 0.0079 1.0000
11.750 1.1250 0.02548 0.02119 0.0252 0.0077 1.0000
12.000 1.1311 0.02664 0.02248 0.0281 0.0076 1.0000
12.250 1.1324 0.02786 0.02383 0.0316 0.0074 1.0000
12.500 1.1303 0.02949 0.02562 0.0349 0.0074 1.0000
12.750 1.1303 0.03107 0.02735 0.0374 0.0073 1.0000
13.000 1.1311 0.03273 0.02912 0.0392 0.0071 1.0000
13.250 1.1235 0.03538 0.03196 0.0407 0.0071 1.0000
13.500 1.1229 0.03761 0.03431 0.0411 0.0069 1.0000
13.750 1.1124 0.04130 0.03820 0.0406 0.0069 1.0000
14.000 1.0981 0.04601 0.04309 0.0389 0.0070 1.0000
14.250 1.0859 0.05104 0.04829 0.0360 0.0069 1.0000
14.500 1.0805 0.05563 0.05298 0.0329 0.0067 1.0000
14.750 1.0414 0.06650 0.06411 0.0257 0.0070 1.0000
15.000 1.0071 0.07755 0.07536 0.0184 0.0070 1.0000
15.250 0.9798 0.08761 0.08554 0.0122 0.0070 1.0000
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