RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Reynolds number: 200,000 Max Cl/Cd: 66.48 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15a213-il-200000-n5.txt Download as CSV file: xf-rg15a213-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6060 0.08680 0.08273 -0.0520 1.0000 0.0171
-13.000 -0.6444 0.07495 0.07076 -0.0592 1.0000 0.0166
-12.750 -0.6785 0.06459 0.06022 -0.0666 1.0000 0.0164
-12.500 -0.7061 0.05697 0.05240 -0.0717 1.0000 0.0161
-12.250 -0.7265 0.05180 0.04705 -0.0744 1.0000 0.0163
-12.000 -0.7473 0.04744 0.04250 -0.0753 1.0000 0.0162
-11.750 -0.7645 0.04434 0.03922 -0.0748 1.0000 0.0164
-11.500 -0.7819 0.04178 0.03652 -0.0726 1.0000 0.0164
-11.250 -0.8014 0.04004 0.03463 -0.0687 1.0000 0.0166
-11.000 -0.8154 0.03826 0.03268 -0.0646 1.0000 0.0167
-10.750 -0.8231 0.03645 0.03063 -0.0610 1.0000 0.0170
-10.500 -0.8259 0.03477 0.02869 -0.0578 1.0000 0.0173
-10.250 -0.8250 0.03306 0.02683 -0.0550 1.0000 0.0176
-10.000 -0.8204 0.03157 0.02525 -0.0524 1.0000 0.0179
-9.750 -0.7966 0.02994 0.02348 -0.0535 0.9971 0.0184
-9.500 -0.7689 0.02842 0.02181 -0.0551 0.9938 0.0190
-9.250 -0.7427 0.02702 0.02024 -0.0561 0.9899 0.0197
-9.000 -0.7144 0.02574 0.01876 -0.0573 0.9862 0.0207
-8.750 -0.6839 0.02455 0.01738 -0.0588 0.9832 0.0216
-8.500 -0.6594 0.02337 0.01616 -0.0592 0.9780 0.0226
-8.250 -0.6303 0.02237 0.01509 -0.0603 0.9739 0.0235
-8.000 -0.5984 0.02143 0.01404 -0.0618 0.9709 0.0245
-7.750 -0.5739 0.02061 0.01311 -0.0617 0.9646 0.0257
-7.500 -0.5437 0.01974 0.01219 -0.0628 0.9605 0.0274
-7.250 -0.5103 0.01901 0.01140 -0.0644 0.9576 0.0293
-7.000 -0.4861 0.01837 0.01067 -0.0640 0.9504 0.0311
-6.750 -0.4543 0.01765 0.00992 -0.0652 0.9464 0.0335
-6.500 -0.4197 0.01702 0.00923 -0.0668 0.9437 0.0381
-6.250 -0.3954 0.01645 0.00867 -0.0664 0.9359 0.0445
-6.000 -0.3625 0.01584 0.00808 -0.0676 0.9319 0.0555
-5.750 -0.3270 0.01531 0.00755 -0.0694 0.9291 0.0688
-5.500 -0.3012 0.01493 0.00718 -0.0691 0.9210 0.0809
-5.250 -0.2667 0.01449 0.00675 -0.0706 0.9167 0.0951
-5.000 -0.2332 0.01404 0.00635 -0.0719 0.9119 0.1115
-4.750 -0.2043 0.01365 0.00601 -0.0723 0.9042 0.1289
-4.500 -0.1689 0.01322 0.00564 -0.0739 0.8994 0.1540
-4.250 -0.1408 0.01283 0.00536 -0.0741 0.8907 0.1840
-4.000 -0.1068 0.01239 0.00503 -0.0755 0.8845 0.2197
-3.750 -0.0776 0.01206 0.00477 -0.0759 0.8753 0.2508
-3.500 -0.0439 0.01167 0.00448 -0.0771 0.8681 0.2912
-3.250 -0.0159 0.01131 0.00427 -0.0773 0.8577 0.3380
-3.000 0.0143 0.01092 0.00406 -0.0778 0.8486 0.3951
-2.750 0.0430 0.01057 0.00389 -0.0780 0.8382 0.4546
-2.500 0.0702 0.01031 0.00381 -0.0778 0.8270 0.5131
-2.250 0.0983 0.01015 0.00380 -0.0775 0.8161 0.5711
-2.000 0.1269 0.01009 0.00380 -0.0773 0.8050 0.6199
-1.750 0.1539 0.01009 0.00380 -0.0768 0.7924 0.6521
-1.500 0.1816 0.01011 0.00377 -0.0765 0.7800 0.6748
-1.250 0.2094 0.01013 0.00374 -0.0762 0.7676 0.6911
-1.000 0.2370 0.01016 0.00371 -0.0759 0.7550 0.7052
-0.750 0.2642 0.01020 0.00369 -0.0754 0.7420 0.7186
-0.500 0.2905 0.01024 0.00370 -0.0748 0.7284 0.7313
-0.250 0.3168 0.01030 0.00370 -0.0742 0.7148 0.7437
0.000 0.3432 0.01036 0.00370 -0.0737 0.7010 0.7557
0.250 0.3691 0.01042 0.00372 -0.0730 0.6873 0.7662
0.500 0.3948 0.01049 0.00375 -0.0724 0.6734 0.7765
0.750 0.4207 0.01057 0.00377 -0.0718 0.6593 0.7873
1.000 0.4457 0.01065 0.00381 -0.0709 0.6451 0.7966
1.250 0.4708 0.01073 0.00385 -0.0702 0.6307 0.8062
1.750 0.5203 0.01091 0.00395 -0.0686 0.6012 0.8243
2.000 0.5452 0.01102 0.00401 -0.0679 0.5860 0.8338
2.250 0.5690 0.01111 0.00408 -0.0669 0.5709 0.8417
2.500 0.5936 0.01123 0.00415 -0.0661 0.5555 0.8505
2.750 0.6172 0.01134 0.00424 -0.0651 0.5401 0.8581
3.000 0.6411 0.01146 0.00433 -0.0643 0.5246 0.8670
3.250 0.6644 0.01159 0.00443 -0.0633 0.5090 0.8760
3.500 0.6877 0.01173 0.00454 -0.0623 0.4934 0.8857
3.750 0.7109 0.01188 0.00467 -0.0613 0.4776 0.8973
4.000 0.7341 0.01203 0.00481 -0.0603 0.4620 0.9105
4.250 0.7584 0.01220 0.00495 -0.0596 0.4461 0.9258
4.500 0.7858 0.01240 0.00513 -0.0596 0.4295 0.9438
4.750 0.8177 0.01263 0.00533 -0.0606 0.4125 0.9674
5.000 0.8476 0.01288 0.00553 -0.0614 0.3954 1.0000
5.250 0.8709 0.01317 0.00577 -0.0608 0.3798 1.0000
5.500 0.8940 0.01347 0.00601 -0.0601 0.3640 1.0000
5.750 0.9167 0.01379 0.00628 -0.0594 0.3479 1.0000
6.000 0.9390 0.01413 0.00658 -0.0585 0.3311 1.0000
6.250 0.9608 0.01449 0.00688 -0.0576 0.3140 1.0000
6.500 0.9822 0.01486 0.00721 -0.0567 0.2973 1.0000
6.750 1.0034 0.01525 0.00756 -0.0557 0.2819 1.0000
7.000 1.0242 0.01566 0.00794 -0.0546 0.2669 1.0000
7.250 1.0446 0.01608 0.00834 -0.0535 0.2533 1.0000
7.500 1.0646 0.01652 0.00876 -0.0524 0.2403 1.0000
7.750 1.0837 0.01699 0.00920 -0.0511 0.2269 1.0000
8.250 1.1187 0.01798 0.01015 -0.0480 0.1993 1.0000
8.500 1.1349 0.01852 0.01067 -0.0463 0.1856 1.0000
8.750 1.1502 0.01911 0.01122 -0.0445 0.1715 1.0000
9.000 1.1649 0.01974 0.01183 -0.0426 0.1576 1.0000
9.250 1.1795 0.02040 0.01246 -0.0408 0.1450 1.0000
9.500 1.1939 0.02107 0.01313 -0.0391 0.1347 1.0000
9.750 1.2071 0.02181 0.01387 -0.0372 0.1254 1.0000
10.000 1.2207 0.02254 0.01462 -0.0355 0.1163 1.0000
10.250 1.2336 0.02333 0.01545 -0.0337 0.1087 1.0000
10.500 1.2449 0.02421 0.01634 -0.0318 0.1013 1.0000
10.750 1.2571 0.02508 0.01726 -0.0301 0.0944 1.0000
11.250 1.2774 0.02711 0.01938 -0.0267 0.0819 1.0000
11.500 1.2845 0.02837 0.02066 -0.0249 0.0760 1.0000
11.750 1.2942 0.02951 0.02189 -0.0234 0.0709 1.0000
12.000 1.3006 0.03092 0.02334 -0.0218 0.0661 1.0000
12.250 1.3070 0.03239 0.02488 -0.0203 0.0622 1.0000
12.500 1.3131 0.03394 0.02652 -0.0190 0.0581 1.0000
12.750 1.3157 0.03583 0.02845 -0.0177 0.0549 1.0000
13.000 1.3198 0.03769 0.03041 -0.0167 0.0520 1.0000
13.250 1.3236 0.03965 0.03250 -0.0158 0.0493 1.0000
13.500 1.3253 0.04190 0.03482 -0.0150 0.0470 1.0000
13.750 1.3237 0.04455 0.03752 -0.0145 0.0451 1.0000
14.000 1.3249 0.04704 0.04013 -0.0141 0.0437 1.0000
14.250 1.3259 0.04964 0.04287 -0.0140 0.0420 1.0000
14.500 1.3256 0.05250 0.04585 -0.0140 0.0408 1.0000
14.750 1.3240 0.05559 0.04906 -0.0142 0.0397 1.0000
15.000 1.3211 0.05898 0.05254 -0.0147 0.0387 1.0000
15.250 1.3164 0.06272 0.05636 -0.0155 0.0378 1.0000
15.500 1.3109 0.06667 0.06038 -0.0164 0.0370 1.0000
15.750 1.3094 0.07022 0.06409 -0.0173 0.0362 1.0000
16.000 1.3069 0.07400 0.06803 -0.0185 0.0353 1.0000
16.250 1.3037 0.07798 0.07214 -0.0198 0.0345 1.0000
16.500 1.2998 0.08220 0.07650 -0.0214 0.0335 1.0000
16.750 1.2950 0.08666 0.08107 -0.0232 0.0327 1.0000
17.000 1.2895 0.09128 0.08579 -0.0251 0.0320 1.0000
17.250 1.2824 0.09629 0.09088 -0.0274 0.0311 1.0000
17.500 1.2753 0.10127 0.09590 -0.0297 0.0303 1.0000
17.750 1.2701 0.10622 0.10103 -0.0321 0.0296 1.0000
18.000 1.2638 0.11141 0.10639 -0.0347 0.0288 1.0000
18.250 1.2571 0.11676 0.11188 -0.0375 0.0279 1.0000
18.500 1.2500 0.12229 0.11753 -0.0406 0.0271 1.0000
18.750 1.2429 0.12783 0.12319 -0.0437 0.0264 1.0000
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Polar data table (+)
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