RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 100 AIRFOIL (rae100-il) Reynolds number: 200,000 Max Cl/Cd: 45.02 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae100-il-200000-n5.txt Download as CSV file: xf-rae100-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 100 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9296 0.08939 0.08523 -0.0060 1.0000 0.0187
-14.000 -0.9860 0.07364 0.06909 -0.0170 1.0000 0.0182
-13.750 -1.0096 0.06562 0.06083 -0.0226 1.0000 0.0181
-13.500 -1.0202 0.06045 0.05555 -0.0260 1.0000 0.0184
-13.250 -1.0347 0.05500 0.04989 -0.0292 1.0000 0.0184
-13.000 -1.0446 0.05071 0.04544 -0.0313 1.0000 0.0185
-12.750 -1.0515 0.04723 0.04181 -0.0325 1.0000 0.0187
-12.500 -1.0575 0.04418 0.03859 -0.0329 1.0000 0.0190
-12.250 -1.0624 0.04153 0.03577 -0.0324 1.0000 0.0192
-12.000 -1.0651 0.03931 0.03339 -0.0311 1.0000 0.0195
-11.750 -1.0664 0.03735 0.03124 -0.0292 1.0000 0.0199
-11.500 -1.0653 0.03556 0.02925 -0.0269 1.0000 0.0203
-11.250 -1.0600 0.03378 0.02726 -0.0250 1.0000 0.0209
-11.000 -1.0508 0.03215 0.02540 -0.0233 1.0000 0.0215
-10.750 -1.0394 0.03063 0.02368 -0.0218 1.0000 0.0222
-10.500 -1.0264 0.02936 0.02238 -0.0205 1.0000 0.0230
-10.250 -1.0110 0.02828 0.02121 -0.0193 1.0000 0.0239
-10.000 -0.9947 0.02716 0.01996 -0.0180 1.0000 0.0250
-9.750 -0.9778 0.02598 0.01863 -0.0168 1.0000 0.0260
-9.500 -0.9598 0.02488 0.01735 -0.0156 1.0000 0.0270
-9.250 -0.9426 0.02372 0.01614 -0.0144 1.0000 0.0282
-9.000 -0.9233 0.02289 0.01526 -0.0134 1.0000 0.0298
-8.750 -0.9033 0.02207 0.01435 -0.0124 1.0000 0.0315
-8.500 -0.8828 0.02126 0.01340 -0.0114 1.0000 0.0333
-8.250 -0.8636 0.02030 0.01241 -0.0102 1.0000 0.0351
-8.000 -0.8426 0.01959 0.01166 -0.0093 1.0000 0.0375
-7.750 -0.8209 0.01895 0.01092 -0.0083 1.0000 0.0404
-7.500 -0.8001 0.01819 0.01012 -0.0073 1.0000 0.0434
-7.250 -0.7783 0.01756 0.00947 -0.0064 1.0000 0.0470
-7.000 -0.7559 0.01701 0.00884 -0.0055 1.0000 0.0512
-6.750 -0.7342 0.01638 0.00823 -0.0045 1.0000 0.0565
-6.500 -0.7117 0.01586 0.00766 -0.0036 1.0000 0.0624
-6.250 -0.6894 0.01533 0.00714 -0.0027 1.0000 0.0702
-6.000 -0.6671 0.01482 0.00665 -0.0017 1.0000 0.0791
-5.750 -0.6446 0.01435 0.00620 -0.0008 1.0000 0.0904
-5.500 -0.6221 0.01389 0.00579 0.0002 1.0000 0.1040
-5.250 -0.5996 0.01345 0.00541 0.0011 1.0000 0.1208
-5.000 -0.5771 0.01305 0.00507 0.0021 1.0000 0.1403
-4.750 -0.5548 0.01262 0.00474 0.0030 1.0000 0.1631
-4.500 -0.5324 0.01223 0.00446 0.0040 1.0000 0.1883
-4.250 -0.5101 0.01187 0.00420 0.0050 1.0000 0.2161
-4.000 -0.4878 0.01153 0.00398 0.0060 1.0000 0.2452
-3.750 -0.4658 0.01121 0.00378 0.0070 1.0000 0.2757
-3.500 -0.4439 0.01092 0.00361 0.0081 1.0000 0.3069
-3.250 -0.4190 0.01065 0.00347 0.0085 0.9985 0.3395
-3.000 -0.3824 0.01037 0.00334 0.0065 0.9895 0.3782
-2.750 -0.3461 0.01012 0.00323 0.0047 0.9800 0.4157
-2.500 -0.3091 0.00988 0.00313 0.0028 0.9700 0.4526
-2.250 -0.2742 0.00967 0.00303 0.0014 0.9571 0.4877
-2.000 -0.2391 0.00947 0.00294 0.0000 0.9429 0.5208
-1.750 -0.2040 0.00929 0.00286 -0.0013 0.9266 0.5531
-1.500 -0.1696 0.00912 0.00279 -0.0024 0.9075 0.5842
-1.250 -0.1370 0.00898 0.00273 -0.0030 0.8846 0.6141
-1.000 -0.1062 0.00887 0.00267 -0.0031 0.8596 0.6428
-0.750 -0.0779 0.00878 0.00262 -0.0027 0.8329 0.6702
-0.500 -0.0513 0.00873 0.00258 -0.0019 0.8051 0.6969
-0.250 -0.0255 0.00870 0.00256 -0.0010 0.7777 0.7239
0.000 0.0000 0.00870 0.00255 0.0000 0.7508 0.7507
0.250 0.0255 0.00870 0.00256 0.0010 0.7240 0.7776
0.500 0.0513 0.00873 0.00258 0.0019 0.6970 0.8052
0.750 0.0778 0.00878 0.00262 0.0027 0.6701 0.8329
1.000 0.1062 0.00887 0.00267 0.0031 0.6428 0.8596
1.250 0.1370 0.00898 0.00273 0.0030 0.6141 0.8846
1.500 0.1697 0.00912 0.00279 0.0024 0.5842 0.9075
1.750 0.2039 0.00929 0.00286 0.0013 0.5530 0.9265
2.000 0.2391 0.00947 0.00294 0.0000 0.5209 0.9429
2.250 0.2743 0.00967 0.00303 -0.0014 0.4876 0.9571
2.500 0.3092 0.00989 0.00313 -0.0028 0.4526 0.9699
2.750 0.3461 0.01012 0.00323 -0.0047 0.4157 0.9798
3.000 0.3824 0.01037 0.00334 -0.0065 0.3784 0.9894
3.250 0.4190 0.01065 0.00348 -0.0085 0.3397 0.9984
3.500 0.4440 0.01092 0.00362 -0.0081 0.3068 1.0000
3.750 0.4659 0.01121 0.00378 -0.0070 0.2755 1.0000
4.000 0.4880 0.01153 0.00397 -0.0060 0.2452 1.0000
4.250 0.5103 0.01187 0.00421 -0.0050 0.2160 1.0000
4.500 0.5326 0.01224 0.00446 -0.0040 0.1881 1.0000
4.750 0.5550 0.01262 0.00474 -0.0031 0.1632 1.0000
5.000 0.5772 0.01305 0.00507 -0.0021 0.1402 1.0000
5.250 0.5998 0.01345 0.00541 -0.0011 0.1208 1.0000
5.500 0.6222 0.01389 0.00579 -0.0002 0.1040 1.0000
5.750 0.6447 0.01435 0.00620 0.0007 0.0903 1.0000
6.000 0.6672 0.01482 0.00665 0.0017 0.0790 1.0000
6.250 0.6895 0.01533 0.00714 0.0026 0.0701 1.0000
6.500 0.7117 0.01586 0.00765 0.0036 0.0624 1.0000
6.750 0.7343 0.01638 0.00823 0.0045 0.0565 1.0000
7.000 0.7559 0.01701 0.00884 0.0055 0.0512 1.0000
7.250 0.7782 0.01756 0.00946 0.0064 0.0470 1.0000
7.500 0.8000 0.01819 0.01013 0.0073 0.0434 1.0000
7.750 0.8207 0.01895 0.01093 0.0084 0.0405 1.0000
8.000 0.8424 0.01960 0.01166 0.0093 0.0376 1.0000
8.250 0.8635 0.02030 0.01241 0.0102 0.0352 1.0000
8.500 0.8826 0.02126 0.01340 0.0114 0.0334 1.0000
8.750 0.9030 0.02208 0.01435 0.0124 0.0316 1.0000
9.000 0.9231 0.02288 0.01526 0.0134 0.0298 1.0000
9.250 0.9424 0.02373 0.01615 0.0144 0.0283 1.0000
9.500 0.9596 0.02487 0.01734 0.0156 0.0270 1.0000
9.750 0.9774 0.02599 0.01863 0.0169 0.0260 1.0000
10.000 0.9943 0.02716 0.01996 0.0181 0.0250 1.0000
10.250 1.0107 0.02826 0.02119 0.0193 0.0239 1.0000
10.500 1.0260 0.02937 0.02239 0.0205 0.0231 1.0000
10.750 1.0391 0.03060 0.02365 0.0219 0.0222 1.0000
11.000 1.0505 0.03212 0.02536 0.0234 0.0215 1.0000
11.250 1.0597 0.03375 0.02723 0.0250 0.0209 1.0000
11.500 1.0652 0.03553 0.02921 0.0270 0.0204 1.0000
11.750 1.0661 0.03732 0.03121 0.0293 0.0199 1.0000
12.000 1.0649 0.03927 0.03335 0.0312 0.0195 1.0000
12.250 1.0624 0.04147 0.03571 0.0324 0.0192 1.0000
12.500 1.0577 0.04411 0.03852 0.0329 0.0190 1.0000
12.750 1.0518 0.04715 0.04172 0.0326 0.0187 1.0000
13.000 1.0451 0.05060 0.04532 0.0314 0.0185 1.0000
13.250 1.0359 0.05478 0.04966 0.0293 0.0184 1.0000
13.500 1.0237 0.05982 0.05488 0.0264 0.0183 1.0000
13.750 1.0090 0.06571 0.06094 0.0225 0.0182 1.0000
14.000 0.9860 0.07365 0.06910 0.0170 0.0182 1.0000
14.250 0.9303 0.08928 0.08511 0.0060 0.0187 1.0000
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