RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Reynolds number: 200,000 Max Cl/Cd: 66.79 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15a111-il-200000.txt Download as CSV file: xf-rg15a111-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RG 15A-1.8/11.0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4716 0.09561 0.09198 -0.0322 1.0000 0.0614
-9.750 -0.4743 0.09151 0.08793 -0.0338 1.0000 0.0627
-9.500 -0.4817 0.08673 0.08320 -0.0364 1.0000 0.0648
-9.250 -0.4092 0.07261 0.06935 -0.0402 1.0000 0.0722
-9.000 -0.4160 0.06818 0.06496 -0.0410 1.0000 0.0734
-8.750 -0.5701 0.04635 0.04269 -0.0516 1.0000 0.0445
-8.500 -0.6568 0.04741 0.04297 -0.0477 1.0000 0.0348
-8.250 -0.6628 0.04293 0.03832 -0.0455 1.0000 0.0338
-8.000 -0.6659 0.03891 0.03399 -0.0429 1.0000 0.0331
-7.750 -0.6649 0.03508 0.02976 -0.0403 1.0000 0.0324
-7.500 -0.6582 0.03201 0.02628 -0.0379 1.0000 0.0326
-7.250 -0.6467 0.02985 0.02373 -0.0358 1.0000 0.0338
-7.000 -0.6328 0.02790 0.02139 -0.0338 1.0000 0.0346
-6.750 -0.6169 0.02607 0.01920 -0.0320 1.0000 0.0351
-6.500 -0.6001 0.02346 0.01628 -0.0305 1.0000 0.0358
-6.250 -0.5818 0.02166 0.01438 -0.0293 1.0000 0.0374
-6.000 -0.5627 0.02092 0.01360 -0.0281 1.0000 0.0401
-5.750 -0.5426 0.02008 0.01264 -0.0269 1.0000 0.0426
-5.500 -0.5220 0.01927 0.01167 -0.0256 1.0000 0.0445
-5.250 -0.5025 0.01788 0.01028 -0.0244 1.0000 0.0475
-5.000 -0.4718 0.01729 0.00967 -0.0254 0.9976 0.0535
-4.750 -0.4338 0.01631 0.00870 -0.0278 0.9935 0.0623
-4.500 -0.3969 0.01538 0.00786 -0.0300 0.9882 0.0850
-4.250 -0.3572 0.01470 0.00736 -0.0329 0.9838 0.1261
-4.000 -0.3218 0.01413 0.00696 -0.0350 0.9774 0.1685
-3.750 -0.2828 0.01352 0.00668 -0.0379 0.9723 0.2370
-3.500 -0.2485 0.01282 0.00642 -0.0398 0.9658 0.3331
-3.250 -0.2128 0.01209 0.00622 -0.0418 0.9598 0.4558
-3.000 -0.1788 0.01162 0.00622 -0.0430 0.9536 0.5725
-2.750 -0.1439 0.01146 0.00623 -0.0440 0.9465 0.6493
-2.500 -0.1022 0.01138 0.00619 -0.0463 0.9427 0.6989
-2.250 -0.0723 0.01132 0.00614 -0.0463 0.9332 0.7321
-2.000 -0.0308 0.01122 0.00605 -0.0483 0.9293 0.7612
-1.750 0.0006 0.01114 0.00597 -0.0484 0.9207 0.7832
-1.500 0.0397 0.01099 0.00582 -0.0500 0.9158 0.8035
-1.250 0.0708 0.01089 0.00569 -0.0500 0.9070 0.8216
-1.000 0.1069 0.01072 0.00551 -0.0509 0.9005 0.8383
-0.750 0.1351 0.01061 0.00539 -0.0503 0.8900 0.8534
-0.500 0.1661 0.01046 0.00523 -0.0501 0.8809 0.8673
-0.250 0.1957 0.01033 0.00507 -0.0497 0.8705 0.8806
0.000 0.2216 0.01023 0.00496 -0.0485 0.8577 0.8937
0.250 0.2483 0.01013 0.00484 -0.0476 0.8447 0.9067
0.500 0.2763 0.01006 0.00473 -0.0470 0.8313 0.9196
0.750 0.3064 0.01000 0.00463 -0.0468 0.8173 0.9320
1.000 0.3390 0.00995 0.00454 -0.0473 0.8024 0.9438
1.250 0.3763 0.00994 0.00447 -0.0489 0.7867 0.9535
1.500 0.4164 0.00993 0.00440 -0.0511 0.7698 0.9614
1.750 0.4549 0.00994 0.00434 -0.0531 0.7522 0.9704
2.000 0.4991 0.00995 0.00429 -0.0564 0.7322 0.9761
2.250 0.5388 0.00997 0.00425 -0.0589 0.7107 0.9840
2.500 0.5801 0.00999 0.00421 -0.0617 0.6887 0.9910
2.750 0.6202 0.01003 0.00418 -0.0644 0.6645 0.9990
3.000 0.6377 0.01010 0.00418 -0.0627 0.6431 1.0000
3.250 0.6510 0.01020 0.00422 -0.0602 0.6219 1.0000
3.500 0.6657 0.01035 0.00427 -0.0578 0.6010 1.0000
3.750 0.6828 0.01051 0.00437 -0.0558 0.5780 1.0000
4.000 0.7029 0.01073 0.00448 -0.0544 0.5548 1.0000
4.250 0.7243 0.01097 0.00464 -0.0531 0.5302 1.0000
4.500 0.7463 0.01122 0.00481 -0.0520 0.5047 1.0000
4.750 0.7685 0.01151 0.00501 -0.0509 0.4787 1.0000
5.000 0.7906 0.01184 0.00523 -0.0499 0.4525 1.0000
5.250 0.8128 0.01217 0.00549 -0.0489 0.4262 1.0000
5.500 0.8351 0.01251 0.00578 -0.0479 0.4000 1.0000
5.750 0.8570 0.01289 0.00608 -0.0468 0.3735 1.0000
6.000 0.8786 0.01331 0.00642 -0.0458 0.3470 1.0000
6.250 0.8998 0.01377 0.00680 -0.0447 0.3206 1.0000
6.500 0.9207 0.01425 0.00719 -0.0436 0.2925 1.0000
6.750 0.9411 0.01477 0.00762 -0.0424 0.2639 1.0000
7.000 0.9612 0.01533 0.00808 -0.0413 0.2359 1.0000
7.250 0.9811 0.01593 0.00862 -0.0401 0.2096 1.0000
7.500 1.0003 0.01659 0.00920 -0.0389 0.1855 1.0000
7.750 1.0185 0.01733 0.00983 -0.0375 0.1633 1.0000
8.000 1.0371 0.01807 0.01053 -0.0362 0.1433 1.0000
8.250 1.0547 0.01887 0.01128 -0.0347 0.1258 1.0000
8.500 1.0712 0.01974 0.01211 -0.0332 0.1104 1.0000
8.750 1.0869 0.02067 0.01302 -0.0315 0.0971 1.0000
9.000 1.1021 0.02166 0.01401 -0.0297 0.0860 1.0000
9.250 1.1157 0.02277 0.01513 -0.0277 0.0769 1.0000
9.500 1.1274 0.02396 0.01626 -0.0256 0.0697 1.0000
9.750 1.1412 0.02497 0.01740 -0.0236 0.0639 1.0000
10.000 1.1522 0.02607 0.01851 -0.0214 0.0588 1.0000
10.250 1.1642 0.02737 0.01992 -0.0194 0.0543 1.0000
10.500 1.1755 0.02832 0.02095 -0.0174 0.0500 1.0000
10.750 1.1849 0.03021 0.02279 -0.0156 0.0460 1.0000
11.000 1.1947 0.03114 0.02394 -0.0134 0.0427 1.0000
11.250 1.2029 0.03234 0.02521 -0.0115 0.0395 1.0000
11.500 1.2109 0.03473 0.02760 -0.0099 0.0364 1.0000
11.750 1.2165 0.03601 0.02911 -0.0079 0.0342 1.0000
12.000 1.2211 0.03752 0.03078 -0.0062 0.0317 1.0000
12.250 1.2260 0.03938 0.03268 -0.0047 0.0300 1.0000
12.500 1.2293 0.04268 0.03611 -0.0033 0.0281 1.0000
12.750 1.2291 0.04500 0.03871 -0.0019 0.0271 1.0000
13.000 1.2279 0.04771 0.04165 -0.0007 0.0260 1.0000
13.250 1.2257 0.05048 0.04461 0.0001 0.0250 1.0000
13.500 1.2222 0.05345 0.04775 0.0005 0.0242 1.0000
13.750 1.2196 0.05629 0.05069 0.0005 0.0234 1.0000
14.000 1.2168 0.05953 0.05400 0.0003 0.0226 1.0000
14.250 1.2077 0.06406 0.05868 -0.0002 0.0220 1.0000
14.750 1.1740 0.07517 0.07027 -0.0037 0.0216 1.0000
15.000 1.1562 0.08114 0.07648 -0.0066 0.0215 1.0000
15.250 1.1386 0.08758 0.08314 -0.0102 0.0214 1.0000
15.500 1.1191 0.09489 0.09066 -0.0144 0.0214 1.0000
15.750 1.0984 0.10296 0.09892 -0.0192 0.0215 1.0000
16.000 1.0760 0.11189 0.10802 -0.0246 0.0217 1.0000
16.250 0.8776 0.18058 0.17714 -0.0649 0.0346 1.0000
16.500 0.8813 0.18548 0.18204 -0.0668 0.0357 1.0000
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