RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG-15 8.9% (rg15-il) Reynolds number: 50,000 Max Cl/Cd: 36.58 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15-il-50000-n5.txt Download as CSV file: xf-rg15-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG-15 8.9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4831 0.09329 0.08622 -0.0290 1.0000 0.0439
-8.750 -0.4854 0.08900 0.08201 -0.0307 1.0000 0.0433
-8.500 -0.4894 0.08463 0.07773 -0.0328 1.0000 0.0427
-8.250 -0.4963 0.08000 0.07319 -0.0352 1.0000 0.0420
-8.000 -0.5051 0.07515 0.06842 -0.0380 1.0000 0.0415
-7.750 -0.5124 0.07037 0.06363 -0.0400 1.0000 0.0409
-7.500 -0.5187 0.06566 0.05887 -0.0415 1.0000 0.0406
-7.250 -0.5223 0.06117 0.05426 -0.0424 1.0000 0.0402
-7.000 -0.5229 0.05680 0.04968 -0.0428 1.0000 0.0408
-6.750 -0.5196 0.05269 0.04530 -0.0429 1.0000 0.0416
-6.500 -0.5131 0.04864 0.04087 -0.0427 1.0000 0.0431
-6.250 -0.5031 0.04473 0.03647 -0.0422 1.0000 0.0445
-6.000 -0.4896 0.04103 0.03222 -0.0415 1.0000 0.0454
-5.750 -0.4729 0.03763 0.02822 -0.0406 1.0000 0.0462
-5.500 -0.4546 0.03457 0.02476 -0.0396 1.0000 0.0474
-5.250 -0.4355 0.03241 0.02243 -0.0388 1.0000 0.0505
-5.000 -0.4147 0.03059 0.02028 -0.0378 1.0000 0.0563
-4.750 -0.3919 0.02852 0.01771 -0.0365 1.0000 0.0599
-4.500 -0.3707 0.02680 0.01594 -0.0353 1.0000 0.0639
-4.250 -0.3486 0.02542 0.01433 -0.0339 1.0000 0.0702
-4.000 -0.3276 0.02427 0.01314 -0.0327 1.0000 0.0816
-3.750 -0.3062 0.02307 0.01187 -0.0314 1.0000 0.0943
-3.500 -0.2844 0.02192 0.01077 -0.0306 1.0000 0.1189
-3.250 -0.2631 0.02067 0.00982 -0.0300 1.0000 0.1732
-3.000 -0.2425 0.01914 0.00900 -0.0296 1.0000 0.3001
-2.750 -0.2276 0.01782 0.00884 -0.0272 1.0000 0.5127
-2.500 -0.2175 0.01752 0.00905 -0.0223 1.0000 0.6858
-2.250 -0.2066 0.01743 0.00905 -0.0177 1.0000 0.7786
-2.000 -0.1925 0.01734 0.00896 -0.0138 1.0000 0.8539
-1.750 -0.1509 0.01726 0.00870 -0.0154 1.0000 0.9413
-1.500 -0.1065 0.01715 0.00822 -0.0194 1.0000 1.0000
-1.250 -0.0923 0.01715 0.00799 -0.0183 1.0000 1.0000
-1.000 -0.0749 0.01724 0.00784 -0.0175 1.0000 1.0000
-0.750 -0.0427 0.01749 0.00786 -0.0195 0.9943 1.0000
-0.500 0.0006 0.01782 0.00792 -0.0234 0.9832 1.0000
-0.250 0.0422 0.01810 0.00800 -0.0270 0.9712 1.0000
0.000 0.0828 0.01834 0.00807 -0.0301 0.9587 1.0000
0.250 0.1228 0.01854 0.00815 -0.0331 0.9457 1.0000
0.500 0.1625 0.01872 0.00823 -0.0358 0.9324 1.0000
0.750 0.2020 0.01887 0.00831 -0.0384 0.9187 1.0000
1.000 0.2415 0.01897 0.00838 -0.0409 0.9048 1.0000
1.250 0.2811 0.01904 0.00844 -0.0433 0.8907 1.0000
1.500 0.3210 0.01908 0.00849 -0.0455 0.8763 1.0000
1.750 0.3593 0.01909 0.00853 -0.0473 0.8612 1.0000
2.000 0.3964 0.01907 0.00855 -0.0487 0.8452 1.0000
2.250 0.4283 0.01910 0.00863 -0.0492 0.8262 1.0000
2.500 0.4624 0.01909 0.00871 -0.0499 0.8076 1.0000
2.750 0.4964 0.01906 0.00874 -0.0504 0.7885 1.0000
3.000 0.5263 0.01910 0.00885 -0.0503 0.7662 1.0000
3.250 0.5568 0.01913 0.00894 -0.0501 0.7436 1.0000
3.500 0.5874 0.01917 0.00909 -0.0499 0.7200 1.0000
3.750 0.6149 0.01929 0.00927 -0.0492 0.6935 1.0000
4.000 0.6420 0.01945 0.00947 -0.0484 0.6658 1.0000
4.250 0.6684 0.01964 0.00969 -0.0474 0.6367 1.0000
4.500 0.6936 0.01989 0.01003 -0.0463 0.6056 1.0000
4.750 0.7176 0.02020 0.01037 -0.0451 0.5723 1.0000
5.000 0.7413 0.02055 0.01072 -0.0438 0.5383 1.0000
5.250 0.7635 0.02098 0.01116 -0.0424 0.5017 1.0000
5.500 0.7852 0.02147 0.01162 -0.0410 0.4640 1.0000
5.750 0.8058 0.02203 0.01220 -0.0394 0.4247 1.0000
6.000 0.8253 0.02269 0.01282 -0.0379 0.3838 1.0000
6.250 0.8440 0.02345 0.01352 -0.0363 0.3418 1.0000
6.500 0.8618 0.02433 0.01432 -0.0347 0.2993 1.0000
6.750 0.8789 0.02536 0.01526 -0.0332 0.2581 1.0000
7.000 0.8955 0.02653 0.01634 -0.0317 0.2183 1.0000
7.250 0.9119 0.02785 0.01759 -0.0303 0.1829 1.0000
7.500 0.9277 0.02931 0.01906 -0.0289 0.1531 1.0000
7.750 0.9436 0.03093 0.02066 -0.0275 0.1294 1.0000
8.000 0.9585 0.03263 0.02233 -0.0261 0.1097 1.0000
8.250 0.9743 0.03451 0.02423 -0.0247 0.0941 1.0000
8.500 0.9893 0.03642 0.02628 -0.0233 0.0797 1.0000
8.750 1.0039 0.03858 0.02848 -0.0219 0.0690 1.0000
9.000 1.0166 0.04062 0.03073 -0.0204 0.0589 1.0000
9.250 1.0323 0.04345 0.03391 -0.0190 0.0521 1.0000
9.500 1.0417 0.04563 0.03611 -0.0176 0.0465 1.0000
9.750 1.0505 0.04866 0.03969 -0.0159 0.0421 1.0000
10.000 1.0570 0.05198 0.04339 -0.0143 0.0397 1.0000
10.250 1.0592 0.05518 0.04689 -0.0125 0.0381 1.0000
10.500 1.0575 0.05821 0.05011 -0.0107 0.0367 1.0000
11.000 1.0420 0.06544 0.05774 -0.0080 0.0350 1.0000
11.250 1.0260 0.06975 0.06236 -0.0077 0.0347 1.0000
11.500 1.0097 0.07456 0.06742 -0.0086 0.0347 1.0000
11.750 0.9921 0.07998 0.07305 -0.0106 0.0348 1.0000
12.000 0.9735 0.08623 0.07947 -0.0139 0.0350 1.0000
12.250 0.9559 0.09305 0.08642 -0.0179 0.0352 1.0000
12.500 0.8955 0.11247 0.10611 -0.0327 0.0397 1.0000
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Polar data table (+)
Polar graphs
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