RG-12 (rg12-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG-12 (rg12-il) Reynolds number: 200,000 Max Cl/Cd: 64.18 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg12-il-200000.txt Download as CSV file: xf-rg12-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RG-12
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 -0.4963 0.10392 0.10026 -0.0201 1.0000 0.0461
-9.750 -0.4969 0.09993 0.09631 -0.0219 1.0000 0.0476
-9.500 -0.5002 0.09555 0.09198 -0.0246 1.0000 0.0493
-9.250 -0.4442 0.07805 0.07479 -0.0362 1.0000 0.0527
-9.000 -0.4341 0.07542 0.07217 -0.0335 1.0000 0.0539
-8.750 -0.4331 0.07192 0.06869 -0.0332 1.0000 0.0550
-8.500 -0.4388 0.06762 0.06443 -0.0343 1.0000 0.0558
-8.250 -0.4508 0.06268 0.05953 -0.0366 1.0000 0.0564
-7.750 -0.5756 0.06196 0.05841 -0.0403 1.0000 0.0538
-7.500 -0.5711 0.05925 0.05571 -0.0390 1.0000 0.0549
-7.250 -0.5690 0.05628 0.05267 -0.0379 1.0000 0.0562
-7.000 -0.5670 0.05308 0.04937 -0.0367 1.0000 0.0581
-6.750 -0.5651 0.04962 0.04565 -0.0355 1.0000 0.0616
-6.500 -0.5682 0.04531 0.04090 -0.0338 1.0000 0.0663
-6.250 -0.5642 0.03571 0.03033 -0.0304 1.0000 0.0409
-6.000 -0.5490 0.03014 0.02403 -0.0272 1.0000 0.0287
-5.750 -0.5327 0.02714 0.02075 -0.0256 1.0000 0.0277
-5.500 -0.5153 0.02426 0.01748 -0.0240 1.0000 0.0274
-5.250 -0.4954 0.02227 0.01515 -0.0224 1.0000 0.0278
-5.000 -0.4743 0.02075 0.01336 -0.0211 1.0000 0.0282
-4.750 -0.4540 0.01844 0.01091 -0.0200 1.0000 0.0313
-4.500 -0.4327 0.01747 0.00985 -0.0188 1.0000 0.0339
-4.250 -0.4108 0.01642 0.00872 -0.0176 1.0000 0.0360
-4.000 -0.3890 0.01560 0.00779 -0.0164 1.0000 0.0393
-3.750 -0.3678 0.01431 0.00655 -0.0153 1.0000 0.0529
-3.500 -0.3465 0.01345 0.00585 -0.0145 1.0000 0.0876
-3.250 -0.3253 0.01279 0.00551 -0.0138 1.0000 0.1455
-3.000 -0.3046 0.01193 0.00522 -0.0133 1.0000 0.2556
-2.750 -0.2740 0.01090 0.00505 -0.0149 0.9967 0.4571
-2.500 -0.2427 0.01028 0.00541 -0.0154 0.9907 0.6933
-2.250 -0.2064 0.01045 0.00570 -0.0165 0.9839 0.7806
-2.000 -0.1735 0.01055 0.00582 -0.0169 0.9757 0.8252
-1.750 -0.1370 0.01069 0.00590 -0.0180 0.9693 0.8595
-1.500 -0.1070 0.01069 0.00587 -0.0177 0.9599 0.8844
-1.250 -0.0749 0.01068 0.00583 -0.0177 0.9519 0.9065
-1.000 -0.0381 0.01066 0.00575 -0.0188 0.9451 0.9265
-0.750 0.0008 0.01064 0.00566 -0.0204 0.9379 0.9430
-0.500 0.0496 0.01062 0.00558 -0.0241 0.9331 0.9560
-0.250 0.1102 0.01058 0.00548 -0.0304 0.9311 0.9634
0.000 0.1652 0.01048 0.00533 -0.0356 0.9260 0.9705
0.250 0.2246 0.01030 0.00513 -0.0418 0.9201 0.9753
0.500 0.2769 0.01008 0.00489 -0.0466 0.9115 0.9808
0.750 0.3277 0.00981 0.00462 -0.0511 0.9001 0.9846
1.000 0.3742 0.00958 0.00438 -0.0548 0.8835 0.9887
1.250 0.4161 0.00939 0.00416 -0.0575 0.8635 0.9932
1.500 0.4561 0.00922 0.00395 -0.0599 0.8401 0.9974
1.750 0.4878 0.00914 0.00383 -0.0606 0.8146 1.0000
2.000 0.5087 0.00913 0.00374 -0.0591 0.7878 1.0000
2.250 0.5286 0.00916 0.00368 -0.0575 0.7607 1.0000
2.500 0.5476 0.00921 0.00365 -0.0557 0.7330 1.0000
2.750 0.5657 0.00929 0.00365 -0.0538 0.7046 1.0000
3.000 0.5832 0.00941 0.00371 -0.0517 0.6760 1.0000
3.250 0.5999 0.00955 0.00377 -0.0496 0.6472 1.0000
3.500 0.6163 0.00972 0.00386 -0.0473 0.6180 1.0000
3.750 0.6327 0.00992 0.00397 -0.0451 0.5880 1.0000
4.000 0.6499 0.01016 0.00410 -0.0430 0.5569 1.0000
4.250 0.6686 0.01043 0.00426 -0.0412 0.5245 1.0000
4.500 0.6887 0.01073 0.00449 -0.0398 0.4898 1.0000
4.750 0.7094 0.01107 0.00472 -0.0384 0.4549 1.0000
5.000 0.7307 0.01144 0.00499 -0.0372 0.4175 1.0000
5.250 0.7519 0.01185 0.00529 -0.0361 0.3788 1.0000
5.500 0.7731 0.01231 0.00562 -0.0349 0.3382 1.0000
5.750 0.7939 0.01284 0.00604 -0.0338 0.2942 1.0000
6.000 0.8142 0.01346 0.00648 -0.0327 0.2484 1.0000
6.250 0.8343 0.01416 0.00699 -0.0316 0.2013 1.0000
6.500 0.8539 0.01497 0.00758 -0.0305 0.1562 1.0000
6.750 0.8731 0.01588 0.00830 -0.0293 0.1175 1.0000
7.000 0.8912 0.01694 0.00919 -0.0279 0.0872 1.0000
7.250 0.9086 0.01814 0.01033 -0.0263 0.0653 1.0000
7.500 0.9259 0.01935 0.01156 -0.0247 0.0516 1.0000
7.750 0.9428 0.02070 0.01294 -0.0230 0.0429 1.0000
8.000 0.9584 0.02229 0.01452 -0.0213 0.0362 1.0000
8.250 0.9782 0.02332 0.01570 -0.0201 0.0311 1.0000
8.500 0.9938 0.02549 0.01789 -0.0185 0.0275 1.0000
8.750 1.0126 0.02794 0.02057 -0.0171 0.0255 1.0000
9.000 1.0312 0.02927 0.02211 -0.0158 0.0229 1.0000
9.250 1.0478 0.03079 0.02381 -0.0144 0.0209 1.0000
9.500 1.0628 0.03306 0.02630 -0.0129 0.0199 1.0000
9.750 1.0751 0.03576 0.02929 -0.0113 0.0193 1.0000
10.000 1.0832 0.03891 0.03276 -0.0093 0.0190 1.0000
10.250 1.0861 0.04232 0.03653 -0.0068 0.0188 1.0000
10.500 1.0851 0.04548 0.04004 -0.0041 0.0189 1.0000
10.750 1.0767 0.04853 0.04343 -0.0007 0.0192 1.0000
11.000 1.0613 0.05201 0.04724 0.0028 0.0195 1.0000
11.250 1.0392 0.05633 0.05192 0.0053 0.0201 1.0000
11.500 1.0101 0.06144 0.05737 0.0059 0.0206 1.0000
11.750 0.9822 0.06737 0.06356 0.0043 0.0210 1.0000
12.000 0.9565 0.07401 0.07042 0.0007 0.0213 1.0000
12.250 0.9292 0.08227 0.07881 -0.0051 0.0217 1.0000
12.500 0.8994 0.09294 0.08963 -0.0132 0.0222 1.0000
12.750 0.8641 0.10768 0.10446 -0.0234 0.0232 1.0000
13.000 0.8393 0.12089 0.11764 -0.0305 0.0247 1.0000
13.250 0.8256 0.13031 0.12702 -0.0351 0.0254 1.0000
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Polar data table (+)
Polar graphs
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