RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG-15 8.9% (rg15-il) Reynolds number: 500,000 Max Cl/Cd: 89.01 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15-il-500000.txt Download as CSV file: xf-rg15-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3834 0.09514 0.09293 -0.0279 1.0000 0.0168
-10.000 -0.3853 0.09049 0.08830 -0.0291 1.0000 0.0168
-7.250 -0.5664 0.04339 0.04060 -0.0420 1.0000 0.0175
-7.000 -0.5660 0.03977 0.03681 -0.0406 1.0000 0.0180
-6.750 -0.5591 0.03691 0.03377 -0.0391 1.0000 0.0183
-6.000 -0.5105 0.02131 0.01656 -0.0377 0.9973 0.0131
-5.750 -0.4787 0.01778 0.01249 -0.0387 0.9954 0.0128
-5.500 -0.4447 0.01627 0.01076 -0.0402 0.9935 0.0137
-5.250 -0.4119 0.01504 0.00936 -0.0413 0.9908 0.0148
-5.000 -0.3775 0.01411 0.00828 -0.0427 0.9880 0.0162
-4.750 -0.3438 0.01263 0.00664 -0.0442 0.9857 0.0191
-4.500 -0.3065 0.01215 0.00615 -0.0464 0.9836 0.0228
-4.250 -0.2729 0.01163 0.00555 -0.0476 0.9800 0.0250
-4.000 -0.2399 0.01074 0.00461 -0.0489 0.9758 0.0299
-3.750 -0.2031 0.01035 0.00417 -0.0508 0.9729 0.0340
-3.500 -0.1652 0.00979 0.00359 -0.0530 0.9707 0.0450
-3.250 -0.1338 0.00909 0.00315 -0.0539 0.9654 0.1038
-3.000 -0.0992 0.00855 0.00288 -0.0556 0.9612 0.1733
-2.750 -0.0621 0.00798 0.00263 -0.0579 0.9584 0.2635
-2.500 -0.0277 0.00730 0.00239 -0.0597 0.9544 0.3931
-2.250 0.0018 0.00652 0.00223 -0.0603 0.9477 0.5644
-2.000 0.0365 0.00617 0.00217 -0.0616 0.9432 0.6666
-1.750 0.0663 0.00603 0.00207 -0.0617 0.9337 0.6997
-1.500 0.0987 0.00590 0.00197 -0.0624 0.9251 0.7271
-1.250 0.1307 0.00580 0.00188 -0.0629 0.9154 0.7526
-1.000 0.1599 0.00574 0.00182 -0.0629 0.9023 0.7712
-0.750 0.1887 0.00570 0.00175 -0.0628 0.8881 0.7873
-0.500 0.2163 0.00569 0.00171 -0.0624 0.8724 0.8027
-0.250 0.2430 0.00568 0.00168 -0.0619 0.8551 0.8173
0.000 0.2694 0.00569 0.00166 -0.0613 0.8369 0.8315
0.250 0.2955 0.00572 0.00164 -0.0606 0.8183 0.8454
0.500 0.3209 0.00575 0.00164 -0.0598 0.7982 0.8595
0.750 0.3457 0.00579 0.00164 -0.0589 0.7778 0.8742
1.000 0.3699 0.00584 0.00166 -0.0578 0.7567 0.8897
1.250 0.3933 0.00589 0.00168 -0.0565 0.7349 0.9067
1.500 0.4161 0.00594 0.00169 -0.0552 0.7123 0.9263
1.750 0.4403 0.00601 0.00171 -0.0541 0.6890 0.9475
2.250 0.5072 0.00625 0.00177 -0.0564 0.6353 0.9836
2.500 0.5452 0.00640 0.00182 -0.0587 0.6055 0.9994
2.750 0.5686 0.00658 0.00188 -0.0580 0.5781 1.0000
3.000 0.5930 0.00679 0.00199 -0.0574 0.5496 1.0000
3.250 0.6178 0.00701 0.00210 -0.0568 0.5195 1.0000
3.500 0.6426 0.00725 0.00223 -0.0563 0.4877 1.0000
3.750 0.6676 0.00750 0.00237 -0.0558 0.4579 1.0000
4.000 0.6925 0.00779 0.00253 -0.0553 0.4263 1.0000
4.250 0.7175 0.00808 0.00273 -0.0549 0.3947 1.0000
4.500 0.7420 0.00842 0.00294 -0.0543 0.3581 1.0000
4.750 0.7664 0.00878 0.00316 -0.0538 0.3210 1.0000
5.000 0.7908 0.00917 0.00342 -0.0533 0.2864 1.0000
5.250 0.8150 0.00959 0.00369 -0.0528 0.2490 1.0000
5.500 0.8390 0.01004 0.00402 -0.0522 0.2146 1.0000
5.750 0.8622 0.01057 0.00438 -0.0516 0.1756 1.0000
6.000 0.8852 0.01115 0.00476 -0.0510 0.1365 1.0000
6.250 0.9083 0.01170 0.00518 -0.0504 0.1067 1.0000
6.500 0.9314 0.01227 0.00562 -0.0497 0.0820 1.0000
6.750 0.9548 0.01278 0.00609 -0.0491 0.0635 1.0000
7.000 0.9780 0.01333 0.00659 -0.0484 0.0494 1.0000
7.250 1.0004 0.01395 0.00714 -0.0477 0.0352 1.0000
7.500 1.0204 0.01490 0.00799 -0.0465 0.0177 1.0000
7.750 1.0416 0.01568 0.00882 -0.0454 0.0134 1.0000
8.000 1.0608 0.01670 0.00995 -0.0440 0.0116 1.0000
8.250 1.0812 0.01752 0.01087 -0.0428 0.0108 1.0000
8.500 1.1006 0.01842 0.01190 -0.0415 0.0100 1.0000
8.750 1.1188 0.01941 0.01299 -0.0401 0.0093 1.0000
9.000 1.1355 0.02055 0.01422 -0.0385 0.0089 1.0000
9.250 1.1498 0.02195 0.01574 -0.0365 0.0085 1.0000
9.500 1.1586 0.02414 0.01811 -0.0340 0.0080 1.0000
9.750 1.1703 0.02607 0.02023 -0.0319 0.0078 1.0000
10.000 1.1861 0.02717 0.02148 -0.0303 0.0075 1.0000
10.250 1.1982 0.02879 0.02329 -0.0284 0.0074 1.0000
10.500 1.2072 0.03067 0.02537 -0.0261 0.0073 1.0000
10.750 1.2120 0.03259 0.02751 -0.0232 0.0072 1.0000
11.000 1.2130 0.03475 0.02991 -0.0201 0.0071 1.0000
11.250 1.2106 0.03711 0.03251 -0.0170 0.0070 1.0000
11.500 1.2053 0.03968 0.03532 -0.0142 0.0069 1.0000
11.750 1.1967 0.04263 0.03851 -0.0118 0.0069 1.0000
12.000 1.1839 0.04618 0.04230 -0.0100 0.0070 1.0000
12.250 1.1706 0.04996 0.04631 -0.0092 0.0068 1.0000
12.500 1.1545 0.05452 0.05110 -0.0095 0.0068 1.0000
12.750 1.1374 0.05974 0.05652 -0.0110 0.0069 1.0000
13.000 1.1195 0.06570 0.06267 -0.0138 0.0069 1.0000
13.250 1.1001 0.07263 0.06980 -0.0177 0.0069 1.0000
13.500 1.0819 0.08006 0.07738 -0.0224 0.0071 1.0000
13.750 1.0624 0.08853 0.08601 -0.0281 0.0071 1.0000
14.000 1.0406 0.09825 0.09588 -0.0345 0.0072 1.0000
14.250 1.0196 0.10869 0.10642 -0.0414 0.0072 1.0000
14.500 0.9970 0.11985 0.11767 -0.0482 0.0075 1.0000
14.750 0.9690 0.13379 0.13171 -0.0564 0.0076 1.0000
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Polar data table (+)
Polar graphs
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