RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.41 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15a213-il-1000000.txt Download as CSV file: xf-rg15a213-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RG 15A 2.5/13.0 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7579 0.09745 0.09518 -0.0466 1.0000 0.0093
-15.750 -0.8102 0.08370 0.08123 -0.0543 1.0000 0.0092
-15.500 -0.8462 0.07353 0.07090 -0.0603 1.0000 0.0091
-15.250 -0.8862 0.06298 0.06012 -0.0667 1.0000 0.0090
-15.000 -0.9039 0.05641 0.05343 -0.0708 1.0000 0.0090
-14.750 -0.9219 0.05022 0.04709 -0.0746 1.0000 0.0090
-14.500 -0.9379 0.04498 0.04170 -0.0774 1.0000 0.0090
-14.250 -0.9430 0.04169 0.03833 -0.0787 1.0000 0.0091
-14.000 -0.9492 0.03866 0.03521 -0.0794 1.0000 0.0092
-13.750 -0.9532 0.03618 0.03265 -0.0794 1.0000 0.0093
-13.500 -0.9591 0.03387 0.03025 -0.0787 1.0000 0.0094
-13.250 -0.9627 0.03211 0.02840 -0.0773 1.0000 0.0095
-13.000 -0.9722 0.03029 0.02649 -0.0749 1.0000 0.0096
-12.750 -0.9849 0.02898 0.02509 -0.0710 1.0000 0.0096
-12.500 -1.0031 0.02810 0.02414 -0.0651 1.0000 0.0097
-12.250 -1.0059 0.02707 0.02302 -0.0614 1.0000 0.0098
-12.000 -0.9905 0.02588 0.02173 -0.0610 0.9991 0.0100
-11.750 -0.9632 0.02463 0.02036 -0.0627 0.9971 0.0102
-11.500 -0.9342 0.02358 0.01920 -0.0644 0.9953 0.0105
-11.250 -0.9037 0.02272 0.01823 -0.0661 0.9940 0.0108
-11.000 -0.8751 0.02221 0.01763 -0.0670 0.9919 0.0110
-10.750 -0.8544 0.02006 0.01534 -0.0678 0.9886 0.0115
-10.500 -0.8248 0.01919 0.01443 -0.0691 0.9867 0.0119
-10.250 -0.7936 0.01848 0.01367 -0.0706 0.9853 0.0122
-10.000 -0.7614 0.01777 0.01290 -0.0722 0.9842 0.0126
-9.750 -0.7283 0.01708 0.01214 -0.0739 0.9833 0.0131
-9.500 -0.7051 0.01646 0.01147 -0.0734 0.9787 0.0134
-9.250 -0.6744 0.01596 0.01090 -0.0744 0.9763 0.0138
-9.000 -0.6436 0.01509 0.00996 -0.0756 0.9743 0.0142
-8.750 -0.6127 0.01408 0.00889 -0.0770 0.9727 0.0150
-8.500 -0.5787 0.01353 0.00831 -0.0786 0.9717 0.0157
-8.250 -0.5517 0.01306 0.00782 -0.0787 0.9678 0.0164
-8.000 -0.5223 0.01263 0.00735 -0.0792 0.9642 0.0170
-7.750 -0.4892 0.01222 0.00690 -0.0804 0.9620 0.0175
-7.500 -0.4567 0.01140 0.00602 -0.0818 0.9601 0.0186
-7.250 -0.4224 0.01091 0.00551 -0.0834 0.9583 0.0195
-7.000 -0.3960 0.01053 0.00510 -0.0831 0.9523 0.0205
-6.750 -0.3648 0.01019 0.00472 -0.0839 0.9476 0.0215
-6.500 -0.3305 0.00971 0.00422 -0.0853 0.9443 0.0236
-6.250 -0.3026 0.00939 0.00388 -0.0854 0.9365 0.0256
-6.000 -0.2699 0.00901 0.00352 -0.0865 0.9304 0.0313
-5.750 -0.2421 0.00859 0.00321 -0.0866 0.9213 0.0515
-5.500 -0.2115 0.00831 0.00297 -0.0872 0.9130 0.0669
-5.250 -0.1839 0.00810 0.00278 -0.0872 0.9022 0.0785
-5.000 -0.1561 0.00792 0.00260 -0.0871 0.8917 0.0895
-4.750 -0.1283 0.00775 0.00243 -0.0871 0.8809 0.1009
-4.500 -0.1016 0.00757 0.00226 -0.0868 0.8691 0.1172
-4.250 -0.0753 0.00737 0.00212 -0.0865 0.8571 0.1416
-4.000 -0.0487 0.00720 0.00199 -0.0863 0.8453 0.1654
-3.750 -0.0224 0.00704 0.00187 -0.0860 0.8331 0.1900
-3.250 0.0300 0.00671 0.00165 -0.0853 0.8077 0.2525
-3.000 0.0562 0.00654 0.00156 -0.0850 0.7949 0.2906
-2.750 0.0822 0.00636 0.00148 -0.0846 0.7821 0.3336
-2.500 0.1082 0.00618 0.00140 -0.0843 0.7694 0.3827
-2.250 0.1341 0.00601 0.00133 -0.0839 0.7561 0.4335
-2.000 0.1599 0.00582 0.00127 -0.0835 0.7427 0.4903
-1.750 0.1858 0.00563 0.00125 -0.0831 0.7296 0.5604
-1.500 0.2122 0.00557 0.00126 -0.0828 0.7161 0.6058
-1.250 0.2392 0.00559 0.00127 -0.0825 0.7027 0.6280
-1.000 0.2662 0.00563 0.00128 -0.0822 0.6891 0.6456
-0.750 0.2932 0.00568 0.00130 -0.0819 0.6755 0.6610
-0.500 0.3202 0.00575 0.00132 -0.0816 0.6615 0.6743
0.000 0.3741 0.00587 0.00138 -0.0810 0.6333 0.6955
0.250 0.4012 0.00595 0.00141 -0.0807 0.6188 0.7036
0.500 0.4282 0.00602 0.00144 -0.0804 0.6043 0.7103
0.750 0.4551 0.00611 0.00148 -0.0801 0.5896 0.7183
1.000 0.4820 0.00620 0.00153 -0.0799 0.5748 0.7263
1.250 0.5086 0.00629 0.00158 -0.0795 0.5596 0.7344
1.500 0.5353 0.00640 0.00164 -0.0792 0.5439 0.7413
1.750 0.5618 0.00649 0.00170 -0.0789 0.5286 0.7482
2.250 0.6147 0.00672 0.00185 -0.0782 0.4974 0.7625
2.500 0.6412 0.00686 0.00193 -0.0779 0.4813 0.7697
2.750 0.6673 0.00697 0.00202 -0.0775 0.4659 0.7767
3.000 0.6935 0.00711 0.00212 -0.0772 0.4505 0.7845
3.250 0.7194 0.00724 0.00222 -0.0767 0.4348 0.7919
3.500 0.7454 0.00739 0.00233 -0.0763 0.4197 0.8000
3.750 0.7711 0.00753 0.00245 -0.0759 0.4043 0.8074
4.000 0.7967 0.00769 0.00257 -0.0755 0.3887 0.8147
4.250 0.8219 0.00787 0.00270 -0.0750 0.3703 0.8218
4.500 0.8465 0.00808 0.00285 -0.0744 0.3514 0.8300
4.750 0.8716 0.00825 0.00300 -0.0739 0.3360 0.8384
5.000 0.8966 0.00842 0.00315 -0.0733 0.3220 0.8479
5.250 0.9211 0.00859 0.00332 -0.0727 0.3081 0.8583
5.500 0.9451 0.00877 0.00349 -0.0720 0.2936 0.8705
5.750 0.9682 0.00897 0.00367 -0.0711 0.2782 0.8852
6.000 0.9902 0.00917 0.00387 -0.0699 0.2627 0.9038
6.250 1.0097 0.00935 0.00405 -0.0682 0.2470 0.9319
6.500 1.0386 0.00958 0.00427 -0.0686 0.2301 0.9875
6.750 1.0632 0.00988 0.00450 -0.0681 0.2147 1.0000
7.000 1.0867 0.01020 0.00475 -0.0675 0.1995 1.0000
7.250 1.1097 0.01054 0.00501 -0.0668 0.1847 1.0000
7.500 1.1325 0.01087 0.00529 -0.0660 0.1710 1.0000
7.750 1.1548 0.01123 0.00557 -0.0652 0.1573 1.0000
8.000 1.1768 0.01158 0.00587 -0.0643 0.1451 1.0000
8.250 1.1985 0.01193 0.00618 -0.0633 0.1341 1.0000
8.500 1.2196 0.01231 0.00652 -0.0622 0.1236 1.0000
8.750 1.2396 0.01273 0.00688 -0.0610 0.1128 1.0000
9.000 1.2597 0.01310 0.00722 -0.0598 0.1042 1.0000
9.250 1.2782 0.01348 0.00758 -0.0582 0.0960 1.0000
9.500 1.2948 0.01394 0.00799 -0.0564 0.0872 1.0000
9.750 1.3124 0.01433 0.00838 -0.0548 0.0808 1.0000
10.000 1.3290 0.01479 0.00881 -0.0530 0.0740 1.0000
10.250 1.3452 0.01525 0.00926 -0.0512 0.0683 1.0000
10.500 1.3612 0.01574 0.00974 -0.0494 0.0623 1.0000
10.750 1.3752 0.01633 0.01030 -0.0473 0.0556 1.0000
11.000 1.3892 0.01691 0.01086 -0.0453 0.0486 1.0000
11.250 1.4016 0.01758 0.01151 -0.0431 0.0423 1.0000
11.500 1.4123 0.01836 0.01225 -0.0408 0.0369 1.0000
11.750 1.4256 0.01899 0.01291 -0.0389 0.0343 1.0000
12.000 1.4360 0.01980 0.01372 -0.0367 0.0317 1.0000
12.250 1.4467 0.02062 0.01458 -0.0347 0.0299 1.0000
12.500 1.4593 0.02134 0.01536 -0.0330 0.0289 1.0000
12.750 1.4703 0.02218 0.01624 -0.0312 0.0278 1.0000
13.000 1.4794 0.02316 0.01726 -0.0292 0.0266 1.0000
13.250 1.4865 0.02431 0.01844 -0.0273 0.0254 1.0000
13.500 1.4921 0.02561 0.01981 -0.0253 0.0245 1.0000
13.750 1.5036 0.02655 0.02081 -0.0240 0.0239 1.0000
14.000 1.5123 0.02773 0.02207 -0.0226 0.0234 1.0000
14.250 1.5206 0.02899 0.02339 -0.0213 0.0228 1.0000
14.500 1.5270 0.03044 0.02491 -0.0200 0.0222 1.0000
14.750 1.5324 0.03204 0.02656 -0.0189 0.0215 1.0000
15.000 1.5351 0.03394 0.02851 -0.0177 0.0209 1.0000
15.250 1.5348 0.03621 0.03086 -0.0167 0.0202 1.0000
15.500 1.5359 0.03846 0.03320 -0.0159 0.0196 1.0000
15.750 1.5414 0.04036 0.03518 -0.0155 0.0194 1.0000
16.000 1.5467 0.04236 0.03727 -0.0152 0.0189 1.0000
16.250 1.5493 0.04472 0.03971 -0.0150 0.0185 1.0000
16.500 1.5518 0.04718 0.04225 -0.0149 0.0180 1.0000
16.750 1.5525 0.04992 0.04507 -0.0151 0.0175 1.0000
17.000 1.5509 0.05306 0.04827 -0.0154 0.0169 1.0000
17.250 1.5461 0.05670 0.05200 -0.0161 0.0165 1.0000
17.500 1.5374 0.06103 0.05642 -0.0171 0.0159 1.0000
17.750 1.5345 0.06470 0.06019 -0.0181 0.0156 1.0000
18.000 1.5336 0.06819 0.06378 -0.0192 0.0152 1.0000
18.250 1.5312 0.07197 0.06766 -0.0205 0.0148 1.0000
18.500 1.5264 0.07622 0.07200 -0.0220 0.0143 1.0000
18.750 1.5195 0.08087 0.07674 -0.0239 0.0138 1.0000
19.000 1.5104 0.08600 0.08196 -0.0260 0.0133 1.0000
19.250 1.4966 0.09203 0.08809 -0.0287 0.0127 1.0000
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