NACA 66 (p51htip-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66 (p51htip-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.81 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51htip-il-1000000.txt Download as CSV file: xf-p51htip-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5396 0.05460 0.05273 -0.0595 0.8792 0.0120
-11.000 -0.5485 0.05132 0.04936 -0.0617 0.8744 0.0122
-10.750 -0.6069 0.05755 0.05545 -0.0689 0.8903 0.0114
-10.500 -0.6345 0.05301 0.05074 -0.0676 0.8801 0.0113
-10.250 -0.6583 0.05018 0.04775 -0.0646 0.8710 0.0111
-10.000 -0.6893 0.04583 0.04318 -0.0594 0.8623 0.0110
-9.750 -0.7256 0.03834 0.03523 -0.0536 0.8554 0.0110
-9.500 -0.7598 0.02918 0.02529 -0.0469 0.8490 0.0110
-9.250 -0.7578 0.02524 0.02084 -0.0437 0.8446 0.0113
-9.000 -0.7446 0.02290 0.01818 -0.0420 0.8410 0.0115
-8.750 -0.7234 0.02224 0.01737 -0.0413 0.8375 0.0116
-8.500 -0.7116 0.01855 0.01325 -0.0394 0.8341 0.0122
-8.250 -0.6886 0.01818 0.01283 -0.0390 0.8310 0.0127
-8.000 -0.6654 0.01758 0.01214 -0.0386 0.8281 0.0130
-7.750 -0.6410 0.01720 0.01171 -0.0383 0.8253 0.0135
-7.500 -0.6167 0.01659 0.01101 -0.0380 0.8225 0.0141
-7.250 -0.5924 0.01585 0.01017 -0.0377 0.8197 0.0146
-7.000 -0.5680 0.01515 0.00935 -0.0373 0.8171 0.0150
-6.750 -0.5430 0.01467 0.00879 -0.0370 0.8145 0.0153
-6.500 -0.5212 0.01339 0.00740 -0.0362 0.8123 0.0160
-6.250 -0.4972 0.01283 0.00684 -0.0358 0.8100 0.0168
-6.000 -0.4719 0.01249 0.00648 -0.0357 0.8077 0.0175
-5.750 -0.4463 0.01219 0.00615 -0.0355 0.8055 0.0184
-5.500 -0.4204 0.01193 0.00586 -0.0353 0.8035 0.0194
-5.250 -0.3946 0.01166 0.00553 -0.0351 0.8015 0.0200
-5.000 -0.3723 0.01099 0.00478 -0.0343 0.7993 0.0210
-4.750 -0.3480 0.01053 0.00432 -0.0339 0.7976 0.0225
-4.500 -0.3220 0.01027 0.00406 -0.0338 0.7958 0.0237
-4.250 -0.2956 0.01005 0.00382 -0.0338 0.7939 0.0252
-4.000 -0.2687 0.00989 0.00365 -0.0338 0.7920 0.0264
-3.750 -0.2439 0.00946 0.00317 -0.0334 0.7902 0.0284
-3.500 -0.2178 0.00921 0.00290 -0.0332 0.7886 0.0307
-3.250 -0.1909 0.00904 0.00271 -0.0332 0.7870 0.0331
-3.000 -0.1637 0.00892 0.00257 -0.0333 0.7854 0.0349
-2.750 -0.1373 0.00869 0.00234 -0.0332 0.7839 0.0416
-2.500 -0.1111 0.00841 0.00217 -0.0331 0.7826 0.0680
-2.250 -0.0929 0.00730 0.00187 -0.0320 0.7810 0.2898
-2.000 -0.0755 0.00615 0.00158 -0.0308 0.7792 0.5281
-1.750 -0.0542 0.00553 0.00152 -0.0298 0.7775 0.6917
-1.500 -0.0265 0.00548 0.00153 -0.0299 0.7761 0.7216
-1.250 0.0011 0.00547 0.00157 -0.0298 0.7748 0.7514
-1.000 0.0288 0.00548 0.00163 -0.0298 0.7735 0.7704
-0.750 0.0572 0.00552 0.00166 -0.0300 0.7722 0.7821
-0.500 0.0853 0.00558 0.00174 -0.0301 0.7707 0.7932
-0.250 0.1133 0.00565 0.00184 -0.0302 0.7693 0.8036
0.000 0.1420 0.00568 0.00188 -0.0304 0.7678 0.8101
0.250 0.1705 0.00566 0.00189 -0.0307 0.7655 0.8149
0.500 0.1992 0.00566 0.00189 -0.0310 0.7629 0.8183
0.750 0.2282 0.00565 0.00188 -0.0313 0.7602 0.8208
1.000 0.2571 0.00565 0.00186 -0.0317 0.7574 0.8233
1.250 0.2859 0.00569 0.00188 -0.0320 0.7542 0.8257
1.500 0.3146 0.00563 0.00187 -0.0323 0.7503 0.8282
1.750 0.3429 0.00556 0.00180 -0.0325 0.7438 0.8305
2.000 0.3710 0.00551 0.00176 -0.0326 0.7352 0.8330
2.250 0.3992 0.00548 0.00171 -0.0327 0.7268 0.8357
2.500 0.4272 0.00543 0.00168 -0.0328 0.7143 0.8387
2.750 0.4546 0.00543 0.00163 -0.0327 0.6954 0.8415
3.000 0.4819 0.00542 0.00164 -0.0327 0.6737 0.8444
3.250 0.5067 0.00558 0.00166 -0.0322 0.6174 0.8474
3.500 0.5182 0.00670 0.00208 -0.0296 0.4542 0.8516
3.750 0.5285 0.00792 0.00259 -0.0269 0.2891 0.8560
4.000 0.5388 0.00902 0.00308 -0.0242 0.1417 0.8606
4.250 0.5532 0.00987 0.00351 -0.0222 0.0475 0.8652
4.500 0.5762 0.01018 0.00378 -0.0215 0.0359 0.8694
4.750 0.5989 0.01047 0.00407 -0.0207 0.0310 0.8737
5.000 0.6213 0.01075 0.00439 -0.0199 0.0280 0.8781
5.250 0.6446 0.01099 0.00466 -0.0192 0.0262 0.8828
5.500 0.6670 0.01127 0.00495 -0.0185 0.0244 0.8875
5.750 0.6857 0.01172 0.00547 -0.0170 0.0225 0.8927
6.000 0.7047 0.01217 0.00598 -0.0155 0.0215 0.8986
6.250 0.7259 0.01243 0.00629 -0.0145 0.0207 0.9042
6.500 0.7458 0.01271 0.00661 -0.0132 0.0197 0.9105
6.750 0.7641 0.01300 0.00694 -0.0117 0.0188 0.9175
7.000 0.7793 0.01334 0.00734 -0.0095 0.0182 0.9259
7.250 0.7918 0.01385 0.00789 -0.0069 0.0172 0.9361
7.500 0.7957 0.01494 0.00911 -0.0028 0.0164 0.9518
7.750 0.8158 0.01531 0.00954 -0.0017 0.0162 0.9666
8.000 0.8441 0.01587 0.01017 -0.0026 0.0158 0.9793
8.250 0.8758 0.01650 0.01085 -0.0042 0.0152 0.9914
8.500 0.8976 0.01715 0.01154 -0.0039 0.0148 1.0000
8.750 0.9172 0.01766 0.01207 -0.0030 0.0143 1.0000
9.000 0.9365 0.01812 0.01257 -0.0021 0.0137 1.0000
9.250 0.9552 0.01874 0.01321 -0.0012 0.0134 1.0000
9.500 0.9733 0.01943 0.01392 -0.0002 0.0131 1.0000
9.750 0.9953 0.02170 0.01631 0.0002 0.0124 1.0000
10.000 1.0137 0.02248 0.01719 0.0011 0.0122 1.0000
10.250 1.0327 0.02351 0.01834 0.0020 0.0120 1.0000
10.500 1.0501 0.02452 0.01947 0.0031 0.0118 1.0000
10.750 1.0665 0.02565 0.02072 0.0043 0.0116 1.0000
11.000 1.0813 0.02696 0.02217 0.0056 0.0113 1.0000
11.250 1.0940 0.02824 0.02359 0.0071 0.0110 1.0000
11.500 1.1046 0.02968 0.02518 0.0088 0.0107 1.0000
11.750 1.1139 0.03088 0.02649 0.0105 0.0105 1.0000
12.000 1.1242 0.03130 0.02694 0.0121 0.0102 1.0000
12.250 1.1301 0.03292 0.02870 0.0140 0.0101 1.0000
12.500 1.1352 0.03439 0.03030 0.0158 0.0099 1.0000
12.750 1.1434 0.03506 0.03099 0.0172 0.0097 1.0000
13.000 1.1419 0.03752 0.03365 0.0193 0.0097 1.0000
13.250 1.1451 0.03893 0.03511 0.0207 0.0095 1.0000
13.500 1.1405 0.04151 0.03785 0.0225 0.0094 1.0000
13.750 1.1213 0.04581 0.04242 0.0247 0.0093 1.0000
14.000 1.0960 0.05081 0.04770 0.0264 0.0092 1.0000
14.250 1.0528 0.05830 0.05554 0.0271 0.0091 1.0000
14.500 1.0356 0.06303 0.06043 0.0266 0.0091 1.0000
14.750 1.0122 0.06915 0.06674 0.0249 0.0091 1.0000
15.000 1.0122 0.07234 0.07000 0.0236 0.0092 1.0000
15.250 0.9797 0.08153 0.07940 0.0190 0.0092 1.0000
15.500 0.9618 0.08938 0.08740 0.0142 0.0093 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66 (p51htip-il)