NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-209 (naca65209-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.04 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65209-il-1000000-n5.txt Download as CSV file: xf-naca65209-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5750 0.14158 0.13983 0.0013 1.0000 0.0031
-12.750 -0.5715 0.13748 0.13574 -0.0004 1.0000 0.0033
-9.750 -0.8654 0.02263 0.01910 -0.0384 1.0000 0.0037
-9.500 -0.8514 0.02045 0.01660 -0.0370 1.0000 0.0039
-9.250 -0.8276 0.01878 0.01468 -0.0373 0.9955 0.0041
-9.000 -0.7997 0.01743 0.01311 -0.0383 0.9898 0.0042
-8.750 -0.7701 0.01639 0.01190 -0.0394 0.9844 0.0043
-8.500 -0.7416 0.01497 0.01027 -0.0404 0.9775 0.0047
-8.250 -0.7115 0.01429 0.00949 -0.0415 0.9702 0.0050
-8.000 -0.6813 0.01383 0.00898 -0.0424 0.9626 0.0054
-7.750 -0.6531 0.01343 0.00852 -0.0429 0.9531 0.0059
-7.500 -0.6267 0.01305 0.00803 -0.0429 0.9430 0.0063
-7.250 -0.6010 0.01267 0.00757 -0.0427 0.9333 0.0068
-7.000 -0.5758 0.01230 0.00710 -0.0424 0.9235 0.0070
-6.750 -0.5518 0.01163 0.00634 -0.0420 0.9134 0.0078
-6.500 -0.5260 0.01138 0.00604 -0.0418 0.9044 0.0083
-6.250 -0.5002 0.01113 0.00574 -0.0416 0.8955 0.0088
-6.000 -0.4742 0.01085 0.00538 -0.0414 0.8868 0.0094
-5.750 -0.4483 0.01054 0.00500 -0.0412 0.8786 0.0101
-5.500 -0.4218 0.01036 0.00476 -0.0411 0.8700 0.0106
-5.250 -0.3950 0.01019 0.00454 -0.0410 0.8620 0.0109
-4.750 -0.3438 0.00921 0.00339 -0.0405 0.8462 0.0130
-4.500 -0.3169 0.00904 0.00318 -0.0405 0.8385 0.0140
-4.250 -0.2899 0.00883 0.00292 -0.0405 0.8305 0.0149
-4.000 -0.2629 0.00861 0.00265 -0.0404 0.8233 0.0156
-3.750 -0.2357 0.00840 0.00239 -0.0404 0.8158 0.0162
-3.500 -0.2084 0.00824 0.00216 -0.0404 0.8087 0.0168
-3.250 -0.1811 0.00803 0.00189 -0.0404 0.8010 0.0179
-3.000 -0.1537 0.00784 0.00168 -0.0404 0.7940 0.0216
-2.750 -0.1260 0.00771 0.00153 -0.0405 0.7870 0.0246
-2.500 -0.0983 0.00761 0.00139 -0.0406 0.7805 0.0266
-2.250 -0.0706 0.00749 0.00125 -0.0406 0.7733 0.0326
-2.000 -0.0429 0.00738 0.00115 -0.0407 0.7667 0.0415
-1.750 -0.0154 0.00713 0.00103 -0.0408 0.7599 0.0885
-1.500 0.0111 0.00658 0.00088 -0.0411 0.7537 0.2215
-1.250 0.0360 0.00552 0.00067 -0.0414 0.7469 0.4842
-1.000 0.0622 0.00508 0.00066 -0.0413 0.7405 0.6234
-0.750 0.0900 0.00498 0.00066 -0.0414 0.7339 0.6609
-0.250 0.1461 0.00494 0.00066 -0.0416 0.7209 0.6962
0.000 0.1740 0.00493 0.00068 -0.0416 0.7142 0.7146
0.250 0.2023 0.00493 0.00070 -0.0418 0.7076 0.7233
0.500 0.2304 0.00495 0.00071 -0.0419 0.7002 0.7300
0.750 0.2585 0.00497 0.00073 -0.0420 0.6899 0.7371
1.000 0.2859 0.00505 0.00075 -0.0419 0.6674 0.7436
1.250 0.3131 0.00515 0.00079 -0.0418 0.6433 0.7507
1.500 0.3399 0.00529 0.00083 -0.0417 0.6053 0.7574
1.750 0.3654 0.00560 0.00090 -0.0413 0.5370 0.7645
2.000 0.3857 0.00665 0.00120 -0.0405 0.3397 0.7717
2.250 0.4070 0.00766 0.00155 -0.0398 0.1626 0.7795
2.500 0.4318 0.00818 0.00178 -0.0395 0.0806 0.7867
2.750 0.4578 0.00850 0.00198 -0.0394 0.0419 0.7943
3.000 0.4846 0.00868 0.00214 -0.0393 0.0314 0.8018
3.250 0.5115 0.00885 0.00233 -0.0392 0.0260 0.8101
3.500 0.5382 0.00903 0.00253 -0.0391 0.0216 0.8180
4.000 0.5916 0.00939 0.00295 -0.0389 0.0174 0.8341
4.250 0.6176 0.00965 0.00325 -0.0386 0.0148 0.8425
4.500 0.6433 0.00996 0.00363 -0.0383 0.0136 0.8516
4.750 0.6691 0.01020 0.00393 -0.0380 0.0133 0.8601
5.000 0.6947 0.01048 0.00427 -0.0377 0.0130 0.8691
5.250 0.7197 0.01078 0.00465 -0.0373 0.0126 0.8790
5.500 0.7444 0.01109 0.00505 -0.0368 0.0122 0.8891
5.750 0.7687 0.01144 0.00547 -0.0362 0.0117 0.8996
6.250 0.8171 0.01201 0.00614 -0.0351 0.0105 0.9220
6.500 0.8402 0.01235 0.00654 -0.0343 0.0100 0.9346
6.750 0.8618 0.01285 0.00713 -0.0333 0.0094 0.9496
7.000 0.8846 0.01365 0.00805 -0.0327 0.0087 0.9720
7.250 0.9131 0.01398 0.00842 -0.0332 0.0084 1.0000
7.500 0.9379 0.01440 0.00889 -0.0329 0.0081 1.0000
7.750 0.9622 0.01489 0.00944 -0.0326 0.0077 1.0000
8.000 0.9864 0.01539 0.01000 -0.0322 0.0073 1.0000
8.250 1.0110 0.01579 0.01043 -0.0320 0.0068 1.0000
8.500 1.0353 0.01620 0.01090 -0.0317 0.0065 1.0000
8.750 1.0599 0.01651 0.01123 -0.0315 0.0061 1.0000
9.000 1.0832 0.01704 0.01178 -0.0311 0.0056 1.0000
9.250 1.1057 0.01769 0.01251 -0.0306 0.0053 1.0000
9.500 1.1283 0.01829 0.01320 -0.0301 0.0051 1.0000
9.750 1.1500 0.01901 0.01402 -0.0294 0.0048 1.0000
10.000 1.1719 0.01965 0.01474 -0.0289 0.0045 1.0000
10.250 1.1932 0.02035 0.01552 -0.0282 0.0043 1.0000
10.500 1.2147 0.02095 0.01619 -0.0276 0.0040 1.0000
10.750 1.2356 0.02160 0.01692 -0.0270 0.0038 1.0000
11.000 1.2550 0.02245 0.01785 -0.0261 0.0036 1.0000
11.250 1.2711 0.02370 0.01925 -0.0249 0.0033 1.0000
11.500 1.2852 0.02515 0.02089 -0.0234 0.0032 1.0000
11.750 1.2983 0.02659 0.02251 -0.0219 0.0031 1.0000
12.000 1.3114 0.02789 0.02397 -0.0204 0.0030 1.0000
12.250 1.3185 0.02960 0.02589 -0.0182 0.0030 1.0000
12.500 1.3213 0.03132 0.02779 -0.0154 0.0029 1.0000
12.750 1.3194 0.03337 0.03006 -0.0123 0.0028 1.0000
13.000 1.3179 0.03539 0.03226 -0.0098 0.0028 1.0000
13.250 1.3129 0.03784 0.03491 -0.0074 0.0027 1.0000
13.500 1.3022 0.04100 0.03829 -0.0053 0.0026 1.0000
13.750 1.2815 0.04545 0.04301 -0.0037 0.0026 1.0000
14.000 1.2582 0.05065 0.04845 -0.0032 0.0026 1.0000
14.250 1.2067 0.06041 0.05857 -0.0053 0.0027 1.0000
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Polar data table (+)
Polar graphs
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