RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Reynolds number: 500,000 Max Cl/Cd: 87.88 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15a111-il-500000.txt Download as CSV file: xf-rg15a111-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5621 0.08831 0.08598 -0.0355 1.0000 0.0164
-11.250 -0.5596 0.08600 0.08369 -0.0368 1.0000 0.0168
-11.000 -0.7510 0.04417 0.04100 -0.0643 1.0000 0.0123
-10.750 -0.7698 0.04185 0.03861 -0.0617 1.0000 0.0125
-10.500 -0.7891 0.03937 0.03596 -0.0577 1.0000 0.0125
-10.250 -0.8016 0.03655 0.03285 -0.0543 1.0000 0.0124
-10.000 -0.8075 0.03390 0.02998 -0.0512 1.0000 0.0125
-9.750 -0.8067 0.03175 0.02764 -0.0485 1.0000 0.0127
-9.500 -0.8026 0.02978 0.02549 -0.0460 1.0000 0.0129
-9.250 -0.7950 0.02813 0.02366 -0.0436 1.0000 0.0131
-9.000 -0.7831 0.02709 0.02253 -0.0417 1.0000 0.0135
-8.750 -0.7714 0.02587 0.02117 -0.0397 1.0000 0.0140
-8.500 -0.7591 0.02453 0.01966 -0.0376 1.0000 0.0145
-8.250 -0.7453 0.02332 0.01825 -0.0357 1.0000 0.0151
-8.000 -0.7202 0.02198 0.01666 -0.0359 0.9988 0.0156
-7.750 -0.6865 0.02094 0.01540 -0.0375 0.9964 0.0160
-7.500 -0.6586 0.01808 0.01230 -0.0387 0.9944 0.0170
-7.250 -0.6267 0.01712 0.01130 -0.0401 0.9918 0.0180
-7.000 -0.5939 0.01628 0.01037 -0.0415 0.9888 0.0190
-6.750 -0.5592 0.01563 0.00964 -0.0432 0.9862 0.0204
-6.500 -0.5250 0.01453 0.00842 -0.0450 0.9841 0.0220
-6.250 -0.4930 0.01376 0.00764 -0.0462 0.9808 0.0238
-6.000 -0.4606 0.01319 0.00702 -0.0473 0.9767 0.0256
-5.750 -0.4251 0.01269 0.00646 -0.0490 0.9738 0.0276
-5.500 -0.3889 0.01196 0.00571 -0.0510 0.9716 0.0316
-5.250 -0.3563 0.01155 0.00525 -0.0521 0.9673 0.0351
-5.000 -0.3240 0.01087 0.00466 -0.0531 0.9626 0.0501
-4.750 -0.2878 0.01032 0.00425 -0.0551 0.9598 0.0799
-4.500 -0.2498 0.00989 0.00391 -0.0574 0.9578 0.1058
-4.250 -0.2184 0.00949 0.00362 -0.0582 0.9523 0.1339
-4.000 -0.1849 0.00906 0.00334 -0.0595 0.9475 0.1723
-3.750 -0.1493 0.00859 0.00305 -0.0613 0.9439 0.2219
-3.500 -0.1200 0.00816 0.00282 -0.0617 0.9362 0.2772
-3.250 -0.0874 0.00764 0.00257 -0.0629 0.9299 0.3534
-3.000 -0.0591 0.00717 0.00237 -0.0631 0.9203 0.4359
-2.750 -0.0288 0.00676 0.00220 -0.0637 0.9117 0.5116
-2.500 -0.0007 0.00649 0.00212 -0.0636 0.9006 0.5809
-2.250 0.0269 0.00637 0.00208 -0.0633 0.8885 0.6294
-2.000 0.0547 0.00631 0.00205 -0.0630 0.8762 0.6625
-1.750 0.0825 0.00629 0.00201 -0.0627 0.8635 0.6869
-1.500 0.1101 0.00629 0.00197 -0.0624 0.8503 0.7051
-1.250 0.1373 0.00630 0.00195 -0.0620 0.8366 0.7209
-1.000 0.1644 0.00632 0.00192 -0.0616 0.8225 0.7352
-0.750 0.1913 0.00635 0.00191 -0.0611 0.8081 0.7483
-0.500 0.2179 0.00638 0.00191 -0.0606 0.7933 0.7603
-0.250 0.2444 0.00641 0.00191 -0.0601 0.7783 0.7714
0.000 0.2710 0.00645 0.00191 -0.0596 0.7630 0.7823
0.250 0.2975 0.00651 0.00191 -0.0591 0.7472 0.7932
0.500 0.3236 0.00655 0.00193 -0.0586 0.7312 0.8031
0.750 0.3498 0.00660 0.00195 -0.0580 0.7145 0.8130
1.250 0.4014 0.00673 0.00201 -0.0568 0.6798 0.8338
1.750 0.4522 0.00688 0.00209 -0.0554 0.6428 0.8554
2.000 0.4772 0.00696 0.00214 -0.0547 0.6232 0.8668
2.250 0.5015 0.00706 0.00220 -0.0538 0.6032 0.8781
2.500 0.5256 0.00714 0.00227 -0.0528 0.5827 0.8906
2.750 0.5490 0.00724 0.00234 -0.0517 0.5615 0.9044
3.000 0.5720 0.00735 0.00241 -0.0505 0.5403 0.9191
3.250 0.5952 0.00745 0.00249 -0.0494 0.5180 0.9358
3.500 0.6213 0.00760 0.00259 -0.0489 0.4952 0.9544
4.250 0.7252 0.00828 0.00299 -0.0539 0.4124 1.0000
4.500 0.7482 0.00852 0.00314 -0.0531 0.3909 1.0000
4.750 0.7720 0.00879 0.00331 -0.0525 0.3666 1.0000
5.000 0.7962 0.00906 0.00351 -0.0519 0.3430 1.0000
5.250 0.8203 0.00937 0.00372 -0.0513 0.3208 1.0000
5.500 0.8445 0.00968 0.00394 -0.0508 0.2962 1.0000
5.750 0.8680 0.01005 0.00420 -0.0501 0.2684 1.0000
6.000 0.8914 0.01043 0.00448 -0.0494 0.2422 1.0000
6.250 0.9146 0.01083 0.00477 -0.0488 0.2182 1.0000
6.500 0.9380 0.01123 0.00508 -0.0481 0.1949 1.0000
6.750 0.9610 0.01166 0.00542 -0.0474 0.1740 1.0000
7.000 0.9838 0.01210 0.00579 -0.0467 0.1535 1.0000
7.250 1.0059 0.01259 0.00619 -0.0458 0.1341 1.0000
7.500 1.0285 0.01304 0.00659 -0.0451 0.1178 1.0000
7.750 1.0506 0.01353 0.00703 -0.0442 0.1027 1.0000
8.000 1.0722 0.01404 0.00749 -0.0433 0.0891 1.0000
8.250 1.0934 0.01458 0.00800 -0.0424 0.0772 1.0000
8.500 1.1138 0.01516 0.00855 -0.0413 0.0664 1.0000
8.750 1.1331 0.01582 0.00916 -0.0401 0.0564 1.0000
9.000 1.1532 0.01639 0.00971 -0.0390 0.0487 1.0000
9.250 1.1730 0.01695 0.01030 -0.0378 0.0429 1.0000
9.500 1.1905 0.01767 0.01101 -0.0363 0.0378 1.0000
9.750 1.2089 0.01827 0.01167 -0.0350 0.0347 1.0000
10.000 1.2269 0.01886 0.01231 -0.0336 0.0318 1.0000
10.250 1.2369 0.01989 0.01335 -0.0310 0.0284 1.0000
10.500 1.2543 0.02035 0.01390 -0.0294 0.0267 1.0000
10.750 1.2686 0.02099 0.01458 -0.0275 0.0244 1.0000
11.000 1.2725 0.02224 0.01587 -0.0242 0.0218 1.0000
11.250 1.2888 0.02277 0.01650 -0.0227 0.0201 1.0000
11.500 1.3011 0.02355 0.01733 -0.0208 0.0183 1.0000
11.750 1.2998 0.02519 0.01903 -0.0175 0.0165 1.0000
12.000 1.3125 0.02599 0.01993 -0.0159 0.0151 1.0000
12.250 1.3208 0.02710 0.02112 -0.0139 0.0141 1.0000
12.500 1.3254 0.02851 0.02259 -0.0119 0.0131 1.0000
12.750 1.3166 0.03102 0.02520 -0.0092 0.0123 1.0000
13.000 1.3219 0.03261 0.02691 -0.0078 0.0118 1.0000
13.250 1.3254 0.03442 0.02885 -0.0065 0.0113 1.0000
13.500 1.3267 0.03654 0.03108 -0.0055 0.0109 1.0000
13.750 1.3277 0.03880 0.03346 -0.0047 0.0105 1.0000
14.000 1.3269 0.04139 0.03615 -0.0043 0.0101 1.0000
14.250 1.3248 0.04426 0.03913 -0.0042 0.0099 1.0000
14.500 1.3190 0.04774 0.04272 -0.0044 0.0097 1.0000
14.750 1.3105 0.05174 0.04684 -0.0051 0.0095 1.0000
15.000 1.2943 0.05696 0.05220 -0.0063 0.0092 1.0000
15.250 1.2849 0.06159 0.05698 -0.0078 0.0090 1.0000
15.500 1.2801 0.06583 0.06136 -0.0094 0.0089 1.0000
15.750 1.2721 0.07070 0.06637 -0.0114 0.0088 1.0000
16.000 1.2640 0.07577 0.07159 -0.0137 0.0087 1.0000
16.250 1.2543 0.08132 0.07728 -0.0164 0.0086 1.0000
16.500 1.2445 0.08705 0.08315 -0.0192 0.0086 1.0000
16.750 1.2345 0.09311 0.08935 -0.0224 0.0083 1.0000
17.000 1.2212 0.09974 0.09613 -0.0258 0.0084 1.0000
17.250 1.2112 0.10616 0.10267 -0.0295 0.0082 1.0000
17.500 1.1958 0.11358 0.11025 -0.0335 0.0083 1.0000
17.750 1.1852 0.12043 0.11722 -0.0375 0.0081 1.0000
18.000 1.1730 0.12765 0.12457 -0.0418 0.0081 1.0000
18.250 1.1585 0.13553 0.13259 -0.0464 0.0081 1.0000
18.500 1.1439 0.14369 0.14088 -0.0513 0.0081 1.0000
18.750 1.1289 0.15218 0.14952 -0.0566 0.0081 1.0000
19.000 1.1132 0.16114 0.15861 -0.0622 0.0081 1.0000
19.250 1.0888 0.17288 0.17052 -0.0694 0.0083 1.0000
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