RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 9.5% AIRFOIL (rg1495-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.98 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg1495-il-1000000-n5.txt Download as CSV file: xf-rg1495-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 9.5% 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -1.0695 0.04994 0.04743 -0.0553 1.0000 0.0040
-14.750 -1.0985 0.04104 0.03831 -0.0632 1.0000 0.0040
-14.500 -1.1132 0.03688 0.03398 -0.0647 1.0000 0.0041
-14.250 -1.1212 0.03421 0.03116 -0.0641 1.0000 0.0041
-14.000 -1.1312 0.03186 0.02865 -0.0622 1.0000 0.0041
-13.750 -1.1383 0.03023 0.02689 -0.0589 1.0000 0.0041
-13.500 -1.1390 0.02886 0.02540 -0.0558 1.0000 0.0042
-13.250 -1.1326 0.02761 0.02403 -0.0536 1.0000 0.0042
-13.000 -1.1262 0.02624 0.02252 -0.0513 1.0000 0.0043
-12.750 -1.1216 0.02457 0.02068 -0.0488 1.0000 0.0045
-12.500 -1.1106 0.02342 0.01940 -0.0468 1.0000 0.0046
-12.250 -1.0974 0.02240 0.01828 -0.0450 1.0000 0.0049
-12.000 -1.0829 0.02149 0.01727 -0.0433 1.0000 0.0050
-11.750 -1.0672 0.02067 0.01636 -0.0417 1.0000 0.0051
-11.500 -1.0505 0.01992 0.01553 -0.0401 1.0000 0.0053
-11.250 -1.0335 0.01918 0.01469 -0.0386 1.0000 0.0055
-11.000 -1.0158 0.01852 0.01394 -0.0371 1.0000 0.0057
-10.750 -0.9976 0.01788 0.01321 -0.0356 1.0000 0.0059
-10.500 -0.9792 0.01724 0.01249 -0.0342 1.0000 0.0061
-10.250 -0.9600 0.01667 0.01184 -0.0328 1.0000 0.0063
-10.000 -0.9311 0.01604 0.01112 -0.0335 0.9989 0.0065
-9.750 -0.9022 0.01533 0.01034 -0.0343 0.9976 0.0070
-9.500 -0.8721 0.01483 0.00979 -0.0351 0.9963 0.0075
-9.250 -0.8414 0.01440 0.00932 -0.0361 0.9951 0.0079
-9.000 -0.8104 0.01400 0.00888 -0.0371 0.9939 0.0085
-8.750 -0.7819 0.01360 0.00843 -0.0374 0.9920 0.0090
-8.500 -0.7524 0.01326 0.00803 -0.0380 0.9901 0.0094
-8.250 -0.7227 0.01274 0.00746 -0.0387 0.9880 0.0102
-8.000 -0.6916 0.01241 0.00712 -0.0396 0.9863 0.0108
-7.750 -0.6597 0.01207 0.00676 -0.0407 0.9848 0.0115
-7.250 -0.6000 0.01144 0.00605 -0.0418 0.9796 0.0127
-7.000 -0.5702 0.01121 0.00578 -0.0423 0.9761 0.0131
-6.750 -0.5395 0.01072 0.00524 -0.0431 0.9732 0.0139
-6.250 -0.4802 0.01003 0.00452 -0.0441 0.9650 0.0155
-6.000 -0.4497 0.00975 0.00421 -0.0447 0.9602 0.0163
-5.750 -0.4173 0.00948 0.00391 -0.0458 0.9560 0.0171
-5.500 -0.3877 0.00923 0.00362 -0.0461 0.9486 0.0176
-5.250 -0.3554 0.00899 0.00335 -0.0471 0.9417 0.0181
-5.000 -0.3254 0.00868 0.00299 -0.0475 0.9311 0.0194
-4.750 -0.2963 0.00845 0.00271 -0.0478 0.9189 0.0206
-4.500 -0.2682 0.00826 0.00248 -0.0478 0.9052 0.0220
-4.250 -0.2410 0.00811 0.00228 -0.0475 0.8907 0.0235
-4.000 -0.2142 0.00797 0.00210 -0.0472 0.8759 0.0271
-3.750 -0.1880 0.00779 0.00191 -0.0468 0.8609 0.0359
-3.500 -0.1619 0.00763 0.00176 -0.0464 0.8455 0.0503
-3.250 -0.1357 0.00751 0.00162 -0.0460 0.8294 0.0617
-3.000 -0.1096 0.00740 0.00150 -0.0456 0.8123 0.0758
-2.750 -0.0834 0.00730 0.00139 -0.0452 0.7948 0.0914
-2.500 -0.0574 0.00717 0.00128 -0.0448 0.7766 0.1139
-2.250 -0.0315 0.00703 0.00119 -0.0444 0.7584 0.1449
-2.000 -0.0054 0.00693 0.00110 -0.0440 0.7405 0.1715
-1.750 0.0201 0.00675 0.00103 -0.0436 0.7219 0.2214
-1.500 0.0455 0.00654 0.00096 -0.0432 0.7029 0.2818
-1.250 0.0710 0.00644 0.00091 -0.0427 0.6797 0.3272
-1.000 0.0967 0.00638 0.00087 -0.0423 0.6532 0.3670
-0.750 0.1220 0.00624 0.00084 -0.0418 0.6291 0.4297
-0.500 0.1470 0.00605 0.00082 -0.0413 0.6066 0.5079
-0.250 0.1721 0.00590 0.00081 -0.0409 0.5834 0.5797
0.000 0.1973 0.00576 0.00081 -0.0403 0.5638 0.6485
0.250 0.2221 0.00562 0.00085 -0.0397 0.5438 0.7224
0.500 0.2477 0.00563 0.00090 -0.0391 0.5228 0.7684
0.750 0.2739 0.00569 0.00096 -0.0387 0.5033 0.7967
1.000 0.3003 0.00577 0.00101 -0.0383 0.4816 0.8143
1.250 0.3269 0.00587 0.00107 -0.0379 0.4623 0.8270
1.500 0.3535 0.00598 0.00113 -0.0376 0.4419 0.8385
1.750 0.3795 0.00611 0.00120 -0.0372 0.4175 0.8503
2.000 0.4056 0.00625 0.00128 -0.0368 0.3927 0.8613
2.250 0.4314 0.00644 0.00137 -0.0363 0.3626 0.8706
2.500 0.4566 0.00666 0.00147 -0.0358 0.3284 0.8794
2.750 0.4819 0.00686 0.00159 -0.0353 0.2998 0.8893
3.000 0.5074 0.00703 0.00170 -0.0347 0.2764 0.9002
3.250 0.5323 0.00721 0.00182 -0.0341 0.2541 0.9116
3.500 0.5564 0.00743 0.00197 -0.0333 0.2263 0.9235
3.750 0.5802 0.00769 0.00213 -0.0325 0.1937 0.9345
4.000 0.6050 0.00794 0.00229 -0.0318 0.1688 0.9437
4.250 0.6306 0.00817 0.00246 -0.0314 0.1515 0.9526
4.500 0.6581 0.00836 0.00262 -0.0314 0.1404 0.9610
4.750 0.6864 0.00857 0.00280 -0.0316 0.1286 0.9697
5.000 0.7171 0.00881 0.00298 -0.0324 0.1141 0.9768
5.250 0.7476 0.00907 0.00318 -0.0331 0.0993 0.9842
5.500 0.7788 0.00936 0.00341 -0.0341 0.0847 0.9905
5.750 0.8095 0.00965 0.00364 -0.0349 0.0743 0.9976
6.000 0.8356 0.00992 0.00388 -0.0347 0.0664 1.0000
6.250 0.8599 0.01014 0.00409 -0.0341 0.0613 1.0000
6.500 0.8840 0.01042 0.00436 -0.0335 0.0553 1.0000
6.750 0.9084 0.01069 0.00461 -0.0329 0.0495 1.0000
7.000 0.9322 0.01101 0.00490 -0.0323 0.0427 1.0000
7.250 0.9565 0.01130 0.00518 -0.0317 0.0379 1.0000
7.500 0.9802 0.01165 0.00551 -0.0311 0.0323 1.0000
7.750 1.0044 0.01195 0.00581 -0.0305 0.0295 1.0000
8.000 1.0279 0.01232 0.00616 -0.0299 0.0258 1.0000
8.250 1.0517 0.01265 0.00651 -0.0293 0.0231 1.0000
8.500 1.0751 0.01301 0.00687 -0.0286 0.0208 1.0000
8.750 1.0982 0.01340 0.00728 -0.0279 0.0184 1.0000
9.000 1.1215 0.01377 0.00766 -0.0273 0.0166 1.0000
9.250 1.1437 0.01422 0.00811 -0.0265 0.0141 1.0000
9.500 1.1662 0.01462 0.00855 -0.0258 0.0123 1.0000
9.750 1.1875 0.01514 0.00906 -0.0248 0.0097 1.0000
10.000 1.2086 0.01565 0.00959 -0.0239 0.0081 1.0000
10.250 1.2289 0.01622 0.01019 -0.0229 0.0068 1.0000
10.500 1.2496 0.01672 0.01075 -0.0219 0.0062 1.0000
10.750 1.2697 0.01726 0.01134 -0.0208 0.0059 1.0000
11.000 1.2887 0.01786 0.01199 -0.0196 0.0054 1.0000
11.250 1.3070 0.01848 0.01266 -0.0183 0.0051 1.0000
11.500 1.3233 0.01924 0.01350 -0.0168 0.0046 1.0000
11.750 1.3403 0.01988 0.01420 -0.0153 0.0045 1.0000
12.000 1.3562 0.02053 0.01494 -0.0137 0.0043 1.0000
12.250 1.3693 0.02118 0.01566 -0.0116 0.0042 1.0000
12.500 1.3808 0.02189 0.01645 -0.0094 0.0040 1.0000
12.750 1.3912 0.02267 0.01731 -0.0070 0.0039 1.0000
13.000 1.4009 0.02350 0.01823 -0.0047 0.0038 1.0000
13.250 1.4095 0.02443 0.01924 -0.0025 0.0037 1.0000
13.500 1.4174 0.02541 0.02030 -0.0003 0.0036 1.0000
13.750 1.4242 0.02651 0.02148 0.0017 0.0035 1.0000
14.000 1.4289 0.02780 0.02287 0.0038 0.0034 1.0000
14.250 1.4324 0.02925 0.02441 0.0056 0.0032 1.0000
14.500 1.4337 0.03097 0.02625 0.0074 0.0031 1.0000
14.750 1.4337 0.03292 0.02830 0.0088 0.0031 1.0000
15.000 1.4313 0.03523 0.03073 0.0099 0.0030 1.0000
15.250 1.4289 0.03773 0.03335 0.0105 0.0029 1.0000
15.500 1.4164 0.04153 0.03731 0.0107 0.0028 1.0000
15.750 1.4155 0.04434 0.04022 0.0103 0.0028 1.0000
16.000 1.4021 0.04893 0.04497 0.0092 0.0028 1.0000
16.250 1.3956 0.05297 0.04913 0.0077 0.0028 1.0000
16.500 1.3883 0.05733 0.05362 0.0059 0.0027 1.0000
16.750 1.3700 0.06372 0.06017 0.0028 0.0027 1.0000
17.000 1.3550 0.06996 0.06654 -0.0005 0.0027 1.0000
17.250 1.3287 0.07856 0.07531 -0.0053 0.0027 1.0000
17.500 1.2973 0.08863 0.08556 -0.0110 0.0027 1.0000
17.750 1.2592 0.10056 0.09768 -0.0179 0.0028 1.0000
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Polar data table (+)
Polar graphs
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