RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.18 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5213-il-1000000.txt Download as CSV file: xf-rae5213-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5213 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5560 0.13461 0.13271 -0.0058 1.0000 0.0141
-12.750 -0.5538 0.13014 0.12824 -0.0076 1.0000 0.0141
-12.500 -0.7841 0.06579 0.06376 -0.0387 1.0000 0.0096
-12.250 -0.7743 0.06312 0.06110 -0.0409 1.0000 0.0097
-12.000 -0.7707 0.05929 0.05724 -0.0443 1.0000 0.0098
-11.750 -0.7720 0.05513 0.05303 -0.0480 1.0000 0.0099
-11.500 -0.7644 0.05313 0.05102 -0.0497 1.0000 0.0099
-11.250 -0.9348 0.02977 0.02624 -0.0558 1.0000 0.0093
-11.000 -0.9306 0.02732 0.02355 -0.0545 1.0000 0.0093
-10.750 -0.9320 0.02363 0.01945 -0.0526 1.0000 0.0094
-10.500 -0.9201 0.02174 0.01734 -0.0513 1.0000 0.0095
-10.250 -0.9045 0.02039 0.01585 -0.0501 1.0000 0.0097
-10.000 -0.8863 0.01947 0.01484 -0.0489 1.0000 0.0098
-9.750 -0.8669 0.01877 0.01409 -0.0479 1.0000 0.0100
-9.500 -0.8471 0.01814 0.01339 -0.0468 1.0000 0.0102
-9.250 -0.8274 0.01748 0.01267 -0.0456 1.0000 0.0104
-9.000 -0.8077 0.01684 0.01195 -0.0444 1.0000 0.0108
-8.750 -0.7883 0.01615 0.01117 -0.0431 1.0000 0.0110
-8.500 -0.7687 0.01552 0.01046 -0.0418 1.0000 0.0113
-8.250 -0.7455 0.01487 0.00972 -0.0412 0.9997 0.0117
-8.000 -0.7129 0.01416 0.00899 -0.0427 0.9982 0.0122
-7.750 -0.6790 0.01388 0.00871 -0.0441 0.9967 0.0128
-7.500 -0.6451 0.01344 0.00821 -0.0456 0.9952 0.0134
-7.250 -0.6114 0.01307 0.00778 -0.0469 0.9935 0.0140
-7.000 -0.5797 0.01238 0.00706 -0.0480 0.9912 0.0147
-6.750 -0.5460 0.01208 0.00677 -0.0494 0.9891 0.0154
-6.500 -0.5116 0.01173 0.00639 -0.0509 0.9874 0.0162
-6.250 -0.4765 0.01150 0.00611 -0.0524 0.9860 0.0170
-6.000 -0.4418 0.01085 0.00549 -0.0541 0.9848 0.0180
-5.750 -0.4104 0.01053 0.00516 -0.0549 0.9811 0.0190
-5.500 -0.3765 0.01026 0.00487 -0.0562 0.9784 0.0199
-5.250 -0.3431 0.00972 0.00432 -0.0575 0.9757 0.0211
-5.000 -0.3120 0.00945 0.00406 -0.0582 0.9709 0.0223
-4.750 -0.2817 0.00923 0.00382 -0.0586 0.9648 0.0233
-4.500 -0.2529 0.00881 0.00340 -0.0588 0.9579 0.0250
-4.250 -0.2235 0.00856 0.00315 -0.0590 0.9506 0.0263
-4.000 -0.1958 0.00831 0.00288 -0.0588 0.9416 0.0277
-3.750 -0.1678 0.00807 0.00263 -0.0587 0.9330 0.0295
-3.500 -0.1407 0.00789 0.00243 -0.0583 0.9216 0.0308
-3.250 -0.1136 0.00769 0.00220 -0.0580 0.9099 0.0328
-3.000 -0.0863 0.00755 0.00203 -0.0576 0.8981 0.0357
-2.750 -0.0592 0.00737 0.00185 -0.0573 0.8859 0.0425
-2.500 -0.0324 0.00705 0.00166 -0.0570 0.8726 0.0787
-2.250 -0.0064 0.00650 0.00145 -0.0568 0.8582 0.1863
-2.000 0.0187 0.00567 0.00120 -0.0567 0.8446 0.3701
-1.750 0.0449 0.00521 0.00110 -0.0564 0.8317 0.4929
-1.500 0.0723 0.00511 0.00109 -0.0562 0.8178 0.5408
-1.250 0.0998 0.00512 0.00108 -0.0558 0.8005 0.5661
-1.000 0.1267 0.00516 0.00107 -0.0553 0.7776 0.5864
-0.750 0.1540 0.00523 0.00109 -0.0549 0.7558 0.6046
-0.500 0.1815 0.00531 0.00112 -0.0546 0.7364 0.6211
-0.250 0.2090 0.00540 0.00118 -0.0542 0.7173 0.6355
0.000 0.2366 0.00547 0.00121 -0.0539 0.6992 0.6457
0.250 0.2644 0.00555 0.00123 -0.0537 0.6808 0.6506
0.500 0.2921 0.00565 0.00124 -0.0534 0.6561 0.6544
0.750 0.3194 0.00577 0.00125 -0.0531 0.6255 0.6581
1.000 0.3456 0.00596 0.00128 -0.0526 0.5775 0.6622
1.250 0.3709 0.00631 0.00136 -0.0521 0.5029 0.6661
1.500 0.3952 0.00683 0.00150 -0.0514 0.4080 0.6700
1.750 0.4190 0.00749 0.00170 -0.0508 0.2967 0.6736
2.000 0.4432 0.00806 0.00189 -0.0502 0.2033 0.6776
2.250 0.4685 0.00849 0.00208 -0.0498 0.1450 0.6817
2.500 0.4953 0.00874 0.00223 -0.0495 0.1219 0.6857
2.750 0.5226 0.00893 0.00236 -0.0493 0.1107 0.6896
3.000 0.5497 0.00913 0.00251 -0.0490 0.1025 0.6933
3.250 0.5771 0.00925 0.00265 -0.0488 0.0980 0.6976
3.500 0.6039 0.00946 0.00282 -0.0486 0.0909 0.7018
3.750 0.6315 0.00958 0.00295 -0.0484 0.0876 0.7061
4.000 0.6587 0.00975 0.00310 -0.0482 0.0835 0.7101
4.250 0.6853 0.00995 0.00330 -0.0479 0.0790 0.7148
4.500 0.7127 0.01005 0.00343 -0.0477 0.0763 0.7195
4.750 0.7396 0.01023 0.00359 -0.0475 0.0724 0.7246
5.000 0.7664 0.01042 0.00378 -0.0472 0.0687 0.7298
5.250 0.7933 0.01055 0.00393 -0.0469 0.0653 0.7354
5.500 0.8196 0.01079 0.00415 -0.0466 0.0614 0.7414
5.750 0.8465 0.01093 0.00432 -0.0464 0.0585 0.7476
6.000 0.8725 0.01117 0.00455 -0.0460 0.0548 0.7552
6.250 0.8990 0.01135 0.00476 -0.0457 0.0518 0.7634
6.500 0.9245 0.01161 0.00503 -0.0453 0.0480 0.7733
6.750 0.9505 0.01180 0.00526 -0.0449 0.0449 0.7845
7.000 0.9755 0.01207 0.00557 -0.0444 0.0414 0.7994
7.250 1.0003 0.01231 0.00587 -0.0438 0.0384 0.8216
7.500 1.0228 0.01247 0.00621 -0.0427 0.0361 0.8729
7.750 1.0497 0.01262 0.00652 -0.0425 0.0340 1.0000
8.000 1.0744 0.01306 0.00695 -0.0420 0.0323 1.0000
8.250 1.0995 0.01340 0.00731 -0.0416 0.0311 1.0000
8.500 1.1242 0.01379 0.00770 -0.0411 0.0300 1.0000
8.750 1.1476 0.01431 0.00823 -0.0404 0.0289 1.0000
9.000 1.1715 0.01477 0.00872 -0.0398 0.0282 1.0000
9.250 1.1956 0.01517 0.00916 -0.0392 0.0276 1.0000
9.500 1.2194 0.01560 0.00961 -0.0386 0.0269 1.0000
9.750 1.2425 0.01607 0.01011 -0.0379 0.0263 1.0000
10.000 1.2649 0.01661 0.01068 -0.0371 0.0258 1.0000
10.250 1.2853 0.01735 0.01145 -0.0361 0.0252 1.0000
10.500 1.3053 0.01811 0.01226 -0.0350 0.0248 1.0000
10.750 1.3271 0.01863 0.01284 -0.0342 0.0246 1.0000
11.000 1.3481 0.01921 0.01348 -0.0332 0.0243 1.0000
11.250 1.3684 0.01983 0.01417 -0.0322 0.0240 1.0000
11.500 1.3879 0.02049 0.01488 -0.0311 0.0237 1.0000
11.750 1.4067 0.02118 0.01563 -0.0299 0.0234 1.0000
12.000 1.4246 0.02189 0.01640 -0.0286 0.0231 1.0000
12.250 1.4414 0.02265 0.01722 -0.0272 0.0229 1.0000
12.500 1.4569 0.02344 0.01807 -0.0257 0.0227 1.0000
12.750 1.4693 0.02427 0.01895 -0.0236 0.0224 1.0000
13.000 1.4783 0.02519 0.01993 -0.0211 0.0222 1.0000
13.250 1.4854 0.02624 0.02106 -0.0186 0.0221 1.0000
13.500 1.4890 0.02761 0.02251 -0.0158 0.0219 1.0000
13.750 1.4900 0.02928 0.02428 -0.0132 0.0217 1.0000
14.000 1.4916 0.03099 0.02611 -0.0109 0.0215 1.0000
14.250 1.4968 0.03241 0.02763 -0.0091 0.0215 1.0000
14.500 1.5018 0.03388 0.02922 -0.0076 0.0214 1.0000
14.750 1.5051 0.03561 0.03105 -0.0062 0.0213 1.0000
15.000 1.5061 0.03765 0.03322 -0.0051 0.0212 1.0000
15.250 1.5066 0.03985 0.03553 -0.0042 0.0211 1.0000
15.500 1.5060 0.04230 0.03810 -0.0037 0.0210 1.0000
15.750 1.5031 0.04514 0.04106 -0.0035 0.0210 1.0000
16.000 1.4985 0.04836 0.04442 -0.0037 0.0209 1.0000
16.250 1.4926 0.05192 0.04812 -0.0044 0.0208 1.0000
16.500 1.4849 0.05596 0.05228 -0.0056 0.0207 1.0000
16.750 1.4758 0.06045 0.05692 -0.0073 0.0206 1.0000
17.000 1.4631 0.06579 0.06240 -0.0098 0.0206 1.0000
17.250 1.4491 0.07177 0.06853 -0.0130 0.0205 1.0000
17.500 1.4314 0.07880 0.07572 -0.0171 0.0205 1.0000
17.750 1.4107 0.08689 0.08397 -0.0221 0.0204 1.0000
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