RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Reynolds number: 500,000 Max Cl/Cd: 93.32 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15a213-il-500000.txt Download as CSV file: xf-rg15a213-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5524 0.10292 0.10042 -0.0422 1.0000 0.0177
-13.250 -0.5517 0.10020 0.09773 -0.0431 1.0000 0.0181
-13.000 -0.6948 0.06422 0.06134 -0.0659 1.0000 0.0157
-12.750 -0.7856 0.04766 0.04414 -0.0774 1.0000 0.0148
-12.500 -0.8023 0.04404 0.04037 -0.0778 1.0000 0.0148
-12.250 -0.8138 0.04153 0.03778 -0.0770 1.0000 0.0149
-12.000 -0.8236 0.03963 0.03580 -0.0752 1.0000 0.0150
-11.750 -0.8438 0.03774 0.03380 -0.0714 1.0000 0.0151
-11.500 -0.8652 0.03643 0.03239 -0.0659 1.0000 0.0151
-11.250 -0.8694 0.03528 0.03118 -0.0624 1.0000 0.0153
-11.000 -0.8731 0.03398 0.02978 -0.0590 1.0000 0.0156
-10.750 -0.8761 0.03246 0.02812 -0.0555 1.0000 0.0157
-10.500 -0.8757 0.03102 0.02652 -0.0524 1.0000 0.0161
-10.250 -0.8507 0.02878 0.02399 -0.0542 0.9973 0.0164
-10.000 -0.8227 0.02689 0.02183 -0.0561 0.9947 0.0168
-9.750 -0.7944 0.02541 0.02010 -0.0575 0.9919 0.0172
-9.500 -0.7652 0.02422 0.01870 -0.0588 0.9886 0.0176
-9.250 -0.7391 0.02176 0.01612 -0.0600 0.9860 0.0183
-9.000 -0.7067 0.02062 0.01491 -0.0618 0.9842 0.0189
-8.750 -0.6761 0.01980 0.01403 -0.0630 0.9813 0.0198
-8.500 -0.6470 0.01899 0.01314 -0.0638 0.9772 0.0207
-8.250 -0.6138 0.01825 0.01230 -0.0653 0.9745 0.0214
-8.000 -0.5817 0.01696 0.01092 -0.0669 0.9724 0.0223
-7.750 -0.5469 0.01603 0.00997 -0.0689 0.9709 0.0234
-7.500 -0.5227 0.01539 0.00929 -0.0684 0.9644 0.0245
-7.250 -0.4888 0.01480 0.00865 -0.0699 0.9615 0.0258
-7.000 -0.4538 0.01402 0.00782 -0.0717 0.9595 0.0275
-6.750 -0.4170 0.01339 0.00718 -0.0738 0.9580 0.0297
-6.500 -0.3910 0.01294 0.00669 -0.0735 0.9515 0.0317
-6.250 -0.3569 0.01234 0.00610 -0.0749 0.9484 0.0361
-6.000 -0.3205 0.01175 0.00555 -0.0768 0.9463 0.0467
-5.750 -0.2832 0.01113 0.00508 -0.0790 0.9445 0.0713
-5.500 -0.2541 0.01078 0.00477 -0.0793 0.9385 0.0855
-5.250 -0.2207 0.01042 0.00444 -0.0804 0.9338 0.0989
-5.000 -0.1847 0.01002 0.00410 -0.0822 0.9303 0.1153
-4.750 -0.1549 0.00970 0.00383 -0.0826 0.9229 0.1349
-4.500 -0.1223 0.00932 0.00354 -0.0837 0.9165 0.1627
-4.250 -0.0919 0.00898 0.00331 -0.0842 0.9084 0.1950
-4.000 -0.0607 0.00864 0.00307 -0.0850 0.9002 0.2306
-3.750 -0.0333 0.00833 0.00288 -0.0849 0.8897 0.2711
-3.500 -0.0041 0.00800 0.00269 -0.0853 0.8802 0.3216
-3.250 0.0231 0.00768 0.00253 -0.0852 0.8691 0.3762
-3.000 0.0493 0.00740 0.00239 -0.0849 0.8573 0.4326
-2.750 0.0758 0.00712 0.00228 -0.0846 0.8458 0.4928
-2.500 0.1021 0.00689 0.00223 -0.0842 0.8342 0.5644
-2.250 0.1286 0.00682 0.00224 -0.0837 0.8218 0.6140
-2.000 0.1554 0.00682 0.00224 -0.0833 0.8091 0.6434
-1.750 0.1825 0.00684 0.00223 -0.0829 0.7964 0.6621
-1.500 0.2096 0.00688 0.00222 -0.0825 0.7838 0.6780
-1.250 0.2365 0.00693 0.00222 -0.0820 0.7709 0.6945
-1.000 0.2633 0.00699 0.00223 -0.0816 0.7577 0.7089
-0.750 0.2898 0.00705 0.00225 -0.0811 0.7441 0.7213
-0.500 0.3163 0.00710 0.00227 -0.0806 0.7305 0.7308
-0.250 0.3431 0.00717 0.00226 -0.0802 0.7167 0.7397
0.000 0.3694 0.00723 0.00229 -0.0797 0.7030 0.7479
0.250 0.3958 0.00730 0.00231 -0.0792 0.6890 0.7571
0.500 0.4219 0.00738 0.00235 -0.0787 0.6750 0.7661
0.750 0.4479 0.00746 0.00239 -0.0781 0.6606 0.7743
1.000 0.4738 0.00755 0.00243 -0.0776 0.6460 0.7824
1.500 0.5253 0.00773 0.00253 -0.0764 0.6163 0.7985
1.750 0.5509 0.00782 0.00259 -0.0759 0.6011 0.8062
2.000 0.5763 0.00792 0.00266 -0.0752 0.5857 0.8142
2.250 0.6015 0.00802 0.00272 -0.0746 0.5701 0.8222
2.500 0.6266 0.00813 0.00280 -0.0739 0.5543 0.8304
2.750 0.6514 0.00824 0.00289 -0.0732 0.5384 0.8383
3.000 0.6762 0.00837 0.00298 -0.0725 0.5226 0.8469
3.250 0.7005 0.00849 0.00308 -0.0718 0.5064 0.8548
3.500 0.7250 0.00863 0.00318 -0.0711 0.4905 0.8633
3.750 0.7489 0.00876 0.00329 -0.0702 0.4746 0.8715
4.250 0.7956 0.00904 0.00354 -0.0683 0.4430 0.8919
4.750 0.8390 0.00932 0.00381 -0.0657 0.4114 0.9197
5.000 0.8596 0.00945 0.00393 -0.0641 0.3946 0.9418
5.250 0.8894 0.00964 0.00410 -0.0646 0.3756 0.9696
5.500 0.9229 0.00990 0.00429 -0.0662 0.3564 1.0000
5.750 0.9481 0.01016 0.00449 -0.0659 0.3406 1.0000
6.000 0.9728 0.01044 0.00471 -0.0655 0.3253 1.0000
6.250 0.9968 0.01072 0.00494 -0.0650 0.3098 1.0000
6.500 1.0203 0.01103 0.00519 -0.0644 0.2940 1.0000
6.750 1.0431 0.01137 0.00546 -0.0636 0.2770 1.0000
7.000 1.0655 0.01172 0.00575 -0.0628 0.2605 1.0000
7.250 1.0871 0.01210 0.00606 -0.0619 0.2436 1.0000
7.500 1.1084 0.01250 0.00638 -0.0609 0.2266 1.0000
7.750 1.1295 0.01289 0.00672 -0.0598 0.2106 1.0000
8.000 1.1500 0.01331 0.00708 -0.0587 0.1955 1.0000
8.250 1.1699 0.01374 0.00746 -0.0575 0.1816 1.0000
8.500 1.1882 0.01419 0.00785 -0.0560 0.1685 1.0000
8.750 1.2062 0.01463 0.00826 -0.0544 0.1557 1.0000
9.000 1.2236 0.01509 0.00869 -0.0528 0.1439 1.0000
9.250 1.2406 0.01557 0.00915 -0.0511 0.1330 1.0000
9.500 1.2567 0.01610 0.00965 -0.0493 0.1232 1.0000
10.000 1.2879 0.01720 0.01073 -0.0457 0.1049 1.0000
10.250 1.3025 0.01781 0.01133 -0.0438 0.0972 1.0000
10.500 1.3161 0.01848 0.01197 -0.0419 0.0892 1.0000
10.750 1.3304 0.01910 0.01262 -0.0401 0.0823 1.0000
11.000 1.3413 0.01993 0.01342 -0.0379 0.0749 1.0000
11.250 1.3540 0.02066 0.01418 -0.0361 0.0683 1.0000
11.500 1.3639 0.02158 0.01510 -0.0339 0.0617 1.0000
11.750 1.3720 0.02263 0.01614 -0.0317 0.0559 1.0000
12.000 1.3805 0.02368 0.01724 -0.0297 0.0513 1.0000
12.250 1.3876 0.02486 0.01843 -0.0276 0.0475 1.0000
12.500 1.3914 0.02631 0.01992 -0.0254 0.0443 1.0000
12.750 1.4005 0.02745 0.02115 -0.0239 0.0424 1.0000
13.000 1.4080 0.02876 0.02249 -0.0224 0.0399 1.0000
13.250 1.4108 0.03047 0.02425 -0.0207 0.0382 1.0000
13.500 1.4111 0.03248 0.02633 -0.0191 0.0366 1.0000
13.750 1.4190 0.03395 0.02790 -0.0182 0.0354 1.0000
14.000 1.4255 0.03559 0.02962 -0.0173 0.0340 1.0000
14.250 1.4292 0.03756 0.03165 -0.0165 0.0328 1.0000
14.500 1.4290 0.03999 0.03413 -0.0158 0.0316 1.0000
14.750 1.4246 0.04295 0.03719 -0.0152 0.0308 1.0000
15.000 1.4205 0.04605 0.04039 -0.0149 0.0300 1.0000
15.250 1.4228 0.04857 0.04303 -0.0149 0.0295 1.0000
15.500 1.4243 0.05129 0.04585 -0.0150 0.0288 1.0000
15.750 1.4233 0.05438 0.04906 -0.0154 0.0282 1.0000
16.000 1.4223 0.05761 0.05239 -0.0159 0.0276 1.0000
16.250 1.4193 0.06119 0.05606 -0.0167 0.0270 1.0000
16.500 1.4151 0.06504 0.06001 -0.0177 0.0264 1.0000
16.750 1.4088 0.06932 0.06437 -0.0190 0.0258 1.0000
17.000 1.3988 0.07421 0.06935 -0.0207 0.0251 1.0000
17.250 1.3875 0.07936 0.07459 -0.0224 0.0246 1.0000
17.500 1.3844 0.08357 0.07893 -0.0241 0.0242 1.0000
17.750 1.3810 0.08791 0.08340 -0.0259 0.0237 1.0000
18.000 1.3760 0.09256 0.08818 -0.0279 0.0232 1.0000
18.250 1.3701 0.09742 0.09315 -0.0301 0.0227 1.0000
18.500 1.3643 0.10240 0.09824 -0.0326 0.0221 1.0000
18.750 1.3576 0.10758 0.10351 -0.0351 0.0216 1.0000
19.000 1.3500 0.11297 0.10899 -0.0379 0.0210 1.0000
19.250 1.3413 0.11854 0.11462 -0.0408 0.0205 1.0000
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Polar data table (+)
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