NACA 66 (p51hroot-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66 (p51hroot-il) Reynolds number: 500,000 Max Cl/Cd: 55.58 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51hroot-il-500000-n5.txt Download as CSV file: xf-p51hroot-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7890 0.08451 0.08148 -0.0678 0.9289 0.0122
-16.500 -0.8216 0.07429 0.07099 -0.0742 0.9184 0.0122
-16.250 -0.8477 0.06656 0.06301 -0.0784 0.9086 0.0122
-16.000 -0.8729 0.05998 0.05617 -0.0811 0.8996 0.0123
-15.750 -0.8880 0.05533 0.05131 -0.0825 0.8912 0.0123
-15.500 -0.8993 0.05160 0.04739 -0.0829 0.8838 0.0124
-15.250 -0.9074 0.04836 0.04399 -0.0830 0.8768 0.0125
-15.000 -0.9146 0.04543 0.04086 -0.0826 0.8702 0.0125
-14.750 -0.9146 0.04340 0.03873 -0.0821 0.8645 0.0126
-14.500 -0.9155 0.04127 0.03646 -0.0813 0.8588 0.0127
-14.250 -0.9149 0.03936 0.03439 -0.0803 0.8536 0.0128
-14.000 -0.9059 0.03846 0.03345 -0.0796 0.8490 0.0131
-13.750 -0.9048 0.03650 0.03133 -0.0784 0.8443 0.0131
-13.500 -0.8997 0.03509 0.02979 -0.0772 0.8397 0.0133
-13.250 -0.8940 0.03368 0.02822 -0.0759 0.8356 0.0135
-13.000 -0.8865 0.03239 0.02681 -0.0747 0.8318 0.0138
-12.750 -0.8776 0.03124 0.02552 -0.0734 0.8278 0.0141
-12.500 -0.8688 0.02989 0.02401 -0.0720 0.8240 0.0144
-12.250 -0.8584 0.02862 0.02254 -0.0707 0.8206 0.0146
-12.000 -0.8463 0.02747 0.02122 -0.0694 0.8175 0.0149
-11.750 -0.8326 0.02640 0.02000 -0.0683 0.8144 0.0151
-11.500 -0.8181 0.02544 0.01891 -0.0672 0.8112 0.0154
-11.250 -0.8036 0.02450 0.01790 -0.0661 0.8082 0.0157
-11.000 -0.7880 0.02376 0.01709 -0.0651 0.8053 0.0160
-10.750 -0.7718 0.02321 0.01647 -0.0640 0.8027 0.0164
-10.500 -0.7546 0.02247 0.01566 -0.0631 0.8002 0.0166
-10.250 -0.7368 0.02191 0.01504 -0.0622 0.7974 0.0170
-10.000 -0.7185 0.02123 0.01429 -0.0613 0.7947 0.0174
-9.750 -0.6999 0.02061 0.01358 -0.0604 0.7921 0.0179
-9.500 -0.6811 0.02001 0.01289 -0.0595 0.7899 0.0184
-9.250 -0.6619 0.01949 0.01226 -0.0586 0.7878 0.0188
-9.000 -0.6438 0.01890 0.01161 -0.0576 0.7858 0.0194
-8.750 -0.6251 0.01833 0.01103 -0.0566 0.7840 0.0198
-8.500 -0.6057 0.01787 0.01054 -0.0557 0.7820 0.0203
-8.250 -0.5858 0.01744 0.01009 -0.0549 0.7800 0.0210
-8.000 -0.5664 0.01697 0.00958 -0.0539 0.7781 0.0215
-7.750 -0.5472 0.01652 0.00907 -0.0528 0.7762 0.0221
-7.500 -0.5274 0.01613 0.00863 -0.0518 0.7744 0.0227
-7.250 -0.5077 0.01576 0.00819 -0.0508 0.7728 0.0232
-7.000 -0.4917 0.01522 0.00763 -0.0491 0.7712 0.0240
-6.750 -0.4739 0.01486 0.00724 -0.0477 0.7697 0.0247
-6.500 -0.4551 0.01455 0.00690 -0.0464 0.7683 0.0254
-6.250 -0.4352 0.01424 0.00659 -0.0453 0.7669 0.0262
-6.000 -0.4140 0.01395 0.00628 -0.0444 0.7654 0.0272
-5.750 -0.3922 0.01368 0.00597 -0.0436 0.7638 0.0280
-5.500 -0.3708 0.01336 0.00563 -0.0427 0.7622 0.0288
-5.250 -0.3495 0.01304 0.00529 -0.0419 0.7606 0.0300
-5.000 -0.3268 0.01278 0.00502 -0.0412 0.7593 0.0314
-4.750 -0.3035 0.01255 0.00478 -0.0407 0.7580 0.0329
-4.500 -0.2796 0.01236 0.00455 -0.0402 0.7569 0.0345
-4.250 -0.2564 0.01211 0.00431 -0.0396 0.7558 0.0378
-4.000 -0.2324 0.01192 0.00411 -0.0392 0.7547 0.0421
-3.750 -0.2090 0.01168 0.00392 -0.0386 0.7537 0.0522
-3.500 -0.1882 0.01129 0.00370 -0.0377 0.7526 0.0920
-3.250 -0.1703 0.01072 0.00346 -0.0364 0.7515 0.1722
-3.000 -0.1551 0.00999 0.00319 -0.0346 0.7503 0.2842
-2.750 -0.1422 0.00914 0.00289 -0.0325 0.7490 0.4190
-2.500 -0.1349 0.00805 0.00262 -0.0291 0.7475 0.6057
-2.250 -0.1114 0.00796 0.00274 -0.0282 0.7462 0.6827
-2.000 -0.0850 0.00800 0.00284 -0.0280 0.7450 0.7104
-1.750 -0.0575 0.00806 0.00292 -0.0280 0.7440 0.7267
-1.500 -0.0297 0.00813 0.00300 -0.0280 0.7430 0.7380
-1.250 -0.0019 0.00822 0.00306 -0.0281 0.7421 0.7488
-1.000 0.0267 0.00827 0.00313 -0.0283 0.7410 0.7543
-0.750 0.0554 0.00825 0.00306 -0.0286 0.7377 0.7580
-0.500 0.0829 0.00815 0.00293 -0.0286 0.7289 0.7606
-0.250 0.1113 0.00809 0.00281 -0.0289 0.7237 0.7626
0.000 0.1400 0.00807 0.00273 -0.0292 0.7201 0.7640
0.250 0.1686 0.00805 0.00273 -0.0296 0.7178 0.7653
0.500 0.1971 0.00803 0.00273 -0.0300 0.7147 0.7665
0.750 0.2257 0.00802 0.00273 -0.0303 0.7118 0.7680
1.000 0.2543 0.00801 0.00274 -0.0307 0.7094 0.7695
1.250 0.2829 0.00800 0.00269 -0.0310 0.7051 0.7711
1.500 0.3106 0.00797 0.00271 -0.0312 0.6986 0.7727
1.750 0.3385 0.00794 0.00266 -0.0313 0.6912 0.7743
2.000 0.3661 0.00792 0.00266 -0.0315 0.6821 0.7761
2.250 0.3932 0.00791 0.00263 -0.0315 0.6695 0.7780
2.500 0.4200 0.00791 0.00261 -0.0315 0.6522 0.7799
2.750 0.4435 0.00798 0.00254 -0.0307 0.6074 0.7816
3.000 0.4513 0.00865 0.00277 -0.0271 0.5131 0.7836
3.250 0.4567 0.00944 0.00320 -0.0233 0.4301 0.7859
3.500 0.4610 0.01019 0.00362 -0.0193 0.3537 0.7884
3.750 0.4640 0.01084 0.00401 -0.0151 0.2874 0.7913
4.000 0.4641 0.01151 0.00441 -0.0103 0.2246 0.7944
4.250 0.4551 0.01279 0.00515 -0.0046 0.1105 0.7980
4.500 0.4597 0.01368 0.00575 -0.0011 0.0405 0.8009
4.750 0.4782 0.01402 0.00608 0.0001 0.0326 0.8036
5.000 0.4977 0.01434 0.00640 0.0011 0.0292 0.8064
5.250 0.5176 0.01465 0.00672 0.0021 0.0267 0.8093
5.500 0.5372 0.01499 0.00706 0.0030 0.0248 0.8123
5.750 0.5574 0.01531 0.00739 0.0039 0.0239 0.8151
6.000 0.5768 0.01564 0.00777 0.0049 0.0227 0.8178
6.250 0.5959 0.01600 0.00816 0.0059 0.0219 0.8209
6.500 0.6147 0.01639 0.00856 0.0069 0.0213 0.8243
6.750 0.6340 0.01677 0.00898 0.0078 0.0211 0.8279
7.000 0.6527 0.01719 0.00942 0.0088 0.0206 0.8314
7.250 0.6710 0.01761 0.00989 0.0098 0.0203 0.8348
7.500 0.6893 0.01804 0.01036 0.0109 0.0199 0.8387
7.750 0.7072 0.01850 0.01087 0.0119 0.0196 0.8429
8.000 0.7250 0.01900 0.01140 0.0129 0.0194 0.8473
8.250 0.7424 0.01948 0.01193 0.0140 0.0191 0.8517
8.500 0.7589 0.02002 0.01250 0.0152 0.0187 0.8568
8.750 0.7750 0.02061 0.01312 0.0163 0.0182 0.8624
9.000 0.7912 0.02119 0.01376 0.0175 0.0179 0.8677
9.250 0.8069 0.02179 0.01442 0.0187 0.0176 0.8736
9.500 0.8221 0.02244 0.01513 0.0199 0.0175 0.8801
9.750 0.8368 0.02311 0.01586 0.0212 0.0171 0.8867
10.000 0.8510 0.02381 0.01663 0.0225 0.0169 0.8946
10.250 0.8646 0.02454 0.01743 0.0239 0.0166 0.9029
10.500 0.8779 0.02530 0.01825 0.0252 0.0164 0.9131
10.750 0.8908 0.02612 0.01915 0.0265 0.0161 0.9252
11.000 0.9048 0.02705 0.02015 0.0274 0.0159 0.9402
11.250 0.9227 0.02827 0.02144 0.0272 0.0156 0.9570
11.500 0.9480 0.02933 0.02260 0.0255 0.0154 0.9783
11.750 0.9623 0.03031 0.02363 0.0262 0.0152 1.0000
12.000 0.9757 0.03134 0.02473 0.0271 0.0150 1.0000
12.250 0.9890 0.03239 0.02584 0.0279 0.0148 1.0000
12.500 1.0018 0.03352 0.02702 0.0288 0.0145 1.0000
12.750 1.0146 0.03467 0.02824 0.0296 0.0144 1.0000
13.000 1.0271 0.03587 0.02950 0.0304 0.0142 1.0000
13.250 1.0392 0.03712 0.03081 0.0312 0.0140 1.0000
13.500 1.0510 0.03841 0.03216 0.0319 0.0138 1.0000
13.750 1.0625 0.03980 0.03357 0.0326 0.0136 1.0000
14.000 1.0752 0.04128 0.03507 0.0333 0.0133 1.0000
14.250 1.0831 0.04297 0.03690 0.0341 0.0130 1.0000
14.500 1.0908 0.04465 0.03872 0.0348 0.0130 1.0000
14.750 1.0961 0.04654 0.04078 0.0356 0.0128 1.0000
15.000 1.1006 0.04860 0.04300 0.0362 0.0126 1.0000
15.250 1.1055 0.05069 0.04522 0.0368 0.0126 1.0000
15.500 1.1068 0.05313 0.04783 0.0373 0.0123 1.0000
15.750 1.1063 0.05591 0.05077 0.0377 0.0122 1.0000
16.000 1.1068 0.05860 0.05360 0.0378 0.0122 1.0000
16.250 1.1040 0.06173 0.05689 0.0378 0.0120 1.0000
16.500 1.0987 0.06533 0.06067 0.0376 0.0119 1.0000
16.750 1.0953 0.06875 0.06422 0.0370 0.0118 1.0000
17.000 1.0874 0.07299 0.06863 0.0361 0.0117 1.0000
17.250 1.0780 0.07761 0.07343 0.0347 0.0117 1.0000
17.500 1.0681 0.08254 0.07852 0.0330 0.0116 1.0000
17.750 1.0593 0.08751 0.08362 0.0309 0.0115 1.0000
18.000 1.0417 0.09427 0.09059 0.0278 0.0115 1.0000
18.250 1.0283 0.10055 0.09702 0.0245 0.0115 1.0000
18.500 1.0093 0.10829 0.10494 0.0202 0.0114 1.0000
18.750 0.9745 0.11998 0.11691 0.0133 0.0115 1.0000
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