NACA 66 (p51hroot-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66 (p51hroot-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.08 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51hroot-il-1000000.txt Download as CSV file: xf-p51hroot-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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9001 0.05318 0.05006 -0.0841 0.9053 0.0129
-15.500 -0.9014 0.05085 0.04763 -0.0842 0.8962 0.0130
-15.250 -0.9158 0.04718 0.04376 -0.0840 0.8877 0.0130
-15.000 -0.9273 0.04396 0.04034 -0.0833 0.8806 0.0130
-14.750 -0.9273 0.04212 0.03840 -0.0826 0.8737 0.0132
-14.500 -0.9368 0.03931 0.03538 -0.0811 0.8674 0.0132
-14.250 -0.9397 0.03713 0.03305 -0.0798 0.8617 0.0133
-14.000 -0.9315 0.03635 0.03222 -0.0788 0.8561 0.0136
-13.750 -0.9355 0.03402 0.02966 -0.0769 0.8508 0.0136
-13.500 -0.9331 0.03235 0.02785 -0.0753 0.8463 0.0138
-13.250 -0.9292 0.03075 0.02610 -0.0737 0.8415 0.0138
-13.000 -0.9223 0.02959 0.02481 -0.0720 0.8368 0.0141
-12.750 -0.9136 0.02847 0.02356 -0.0705 0.8328 0.0143
-12.500 -0.9047 0.02713 0.02208 -0.0689 0.8290 0.0146
-12.250 -0.8938 0.02599 0.02080 -0.0675 0.8250 0.0148
-12.000 -0.8813 0.02518 0.01986 -0.0660 0.8211 0.0150
-11.750 -0.8676 0.02417 0.01871 -0.0647 0.8175 0.0151
-11.500 -0.8538 0.02287 0.01727 -0.0635 0.8145 0.0156
-11.250 -0.8377 0.02176 0.01609 -0.0625 0.8115 0.0159
-11.000 -0.8217 0.02128 0.01558 -0.0614 0.8084 0.0163
-10.750 -0.8056 0.02094 0.01520 -0.0602 0.8054 0.0167
-10.500 -0.7874 0.02021 0.01438 -0.0592 0.8022 0.0169
-10.250 -0.7697 0.01979 0.01392 -0.0582 0.8000 0.0174
-10.000 -0.7502 0.01914 0.01321 -0.0573 0.7977 0.0177
-9.750 -0.7307 0.01859 0.01260 -0.0565 0.7954 0.0182
-9.500 -0.7111 0.01814 0.01208 -0.0556 0.7931 0.0186
-9.250 -0.6913 0.01778 0.01164 -0.0546 0.7909 0.0189
-9.000 -0.6725 0.01664 0.01045 -0.0537 0.7888 0.0197
-8.750 -0.6535 0.01614 0.00992 -0.0527 0.7865 0.0202
-8.500 -0.6336 0.01575 0.00951 -0.0518 0.7846 0.0207
-8.250 -0.6132 0.01539 0.00914 -0.0509 0.7830 0.0213
-8.000 -0.5931 0.01499 0.00871 -0.0500 0.7813 0.0218
-7.750 -0.5729 0.01462 0.00831 -0.0489 0.7796 0.0224
-7.500 -0.5522 0.01434 0.00799 -0.0480 0.7779 0.0229
-7.250 -0.5327 0.01400 0.00761 -0.0468 0.7763 0.0234
-7.000 -0.5195 0.01333 0.00690 -0.0445 0.7745 0.0243
-6.750 -0.5004 0.01298 0.00654 -0.0433 0.7728 0.0250
-6.500 -0.4792 0.01269 0.00622 -0.0424 0.7710 0.0256
-6.250 -0.4570 0.01245 0.00595 -0.0416 0.7692 0.0264
-6.000 -0.4342 0.01219 0.00568 -0.0410 0.7683 0.0274
-5.750 -0.4112 0.01193 0.00541 -0.0404 0.7672 0.0279
-5.500 -0.3878 0.01169 0.00515 -0.0399 0.7661 0.0285
-5.250 -0.3681 0.01121 0.00465 -0.0387 0.7649 0.0301
-5.000 -0.3446 0.01096 0.00439 -0.0381 0.7637 0.0315
-4.750 -0.3203 0.01074 0.00416 -0.0377 0.7625 0.0327
-4.500 -0.2955 0.01055 0.00396 -0.0374 0.7614 0.0340
-4.250 -0.2710 0.01033 0.00372 -0.0371 0.7603 0.0358
-4.000 -0.2466 0.01010 0.00350 -0.0366 0.7593 0.0393
-3.750 -0.2213 0.00992 0.00333 -0.0364 0.7583 0.0437
-3.500 -0.1997 0.00952 0.00311 -0.0356 0.7572 0.0807
-3.250 -0.1866 0.00862 0.00277 -0.0334 0.7559 0.2237
-3.000 -0.1740 0.00768 0.00245 -0.0312 0.7544 0.3844
-2.750 -0.1612 0.00674 0.00215 -0.0290 0.7529 0.5508
-2.500 -0.1408 0.00630 0.00213 -0.0278 0.7522 0.6673
-2.250 -0.1131 0.00629 0.00216 -0.0279 0.7515 0.6929
-2.000 -0.0848 0.00631 0.00221 -0.0281 0.7508 0.7102
-1.750 -0.0565 0.00627 0.00219 -0.0283 0.7478 0.7221
-1.500 -0.0283 0.00620 0.00206 -0.0283 0.7412 0.7327
-1.250 -0.0002 0.00625 0.00210 -0.0283 0.7362 0.7433
-1.000 0.0284 0.00625 0.00210 -0.0286 0.7336 0.7499
-0.750 0.0571 0.00627 0.00215 -0.0288 0.7306 0.7569
-0.500 0.0858 0.00629 0.00214 -0.0291 0.7262 0.7626
-0.250 0.1146 0.00629 0.00210 -0.0294 0.7221 0.7660
0.000 0.1435 0.00625 0.00208 -0.0297 0.7183 0.7688
0.250 0.1726 0.00623 0.00207 -0.0302 0.7152 0.7706
0.500 0.2016 0.00618 0.00201 -0.0306 0.7099 0.7722
0.750 0.2304 0.00619 0.00198 -0.0309 0.7049 0.7737
1.000 0.2595 0.00615 0.00196 -0.0314 0.7005 0.7751
1.250 0.2884 0.00612 0.00193 -0.0318 0.6944 0.7764
1.500 0.3169 0.00612 0.00189 -0.0321 0.6881 0.7778
1.750 0.3457 0.00610 0.00189 -0.0326 0.6795 0.7792
2.000 0.3741 0.00612 0.00188 -0.0329 0.6707 0.7806
2.250 0.4023 0.00612 0.00186 -0.0331 0.6590 0.7821
2.500 0.4296 0.00613 0.00186 -0.0333 0.6376 0.7838
2.750 0.4431 0.00677 0.00207 -0.0308 0.5353 0.7858
3.000 0.4509 0.00768 0.00252 -0.0274 0.4263 0.7881
3.250 0.4573 0.00852 0.00294 -0.0238 0.3262 0.7906
3.500 0.4632 0.00928 0.00332 -0.0201 0.2387 0.7931
3.750 0.4669 0.00994 0.00367 -0.0160 0.1652 0.7957
4.000 0.4655 0.01066 0.00409 -0.0109 0.0918 0.7981
4.250 0.4738 0.01125 0.00450 -0.0077 0.0422 0.8013
4.500 0.4918 0.01156 0.00478 -0.0063 0.0325 0.8038
4.750 0.5115 0.01184 0.00505 -0.0052 0.0286 0.8063
5.000 0.5311 0.01212 0.00533 -0.0041 0.0264 0.8090
5.250 0.5507 0.01242 0.00563 -0.0030 0.0251 0.8117
5.500 0.5710 0.01271 0.00592 -0.0021 0.0244 0.8143
5.750 0.5907 0.01298 0.00623 -0.0010 0.0241 0.8177
6.000 0.6103 0.01328 0.00656 0.0000 0.0234 0.8209
6.250 0.6296 0.01361 0.00691 0.0011 0.0231 0.8242
6.500 0.6486 0.01397 0.00728 0.0021 0.0227 0.8277
6.750 0.6680 0.01433 0.00765 0.0031 0.0224 0.8310
7.000 0.6856 0.01473 0.00809 0.0044 0.0217 0.8349
7.250 0.7028 0.01517 0.00857 0.0057 0.0215 0.8390
7.500 0.7210 0.01560 0.00903 0.0068 0.0212 0.8432
7.750 0.7399 0.01600 0.00945 0.0077 0.0209 0.8473
8.000 0.7574 0.01644 0.00994 0.0089 0.0206 0.8518
8.250 0.7750 0.01688 0.01043 0.0100 0.0204 0.8567
8.500 0.7917 0.01740 0.01099 0.0112 0.0201 0.8618
8.750 0.8095 0.01787 0.01149 0.0123 0.0197 0.8669
9.000 0.8260 0.01836 0.01203 0.0135 0.0194 0.8726
9.250 0.8422 0.01891 0.01262 0.0147 0.0191 0.8789
9.500 0.8571 0.01952 0.01328 0.0161 0.0189 0.8854
9.750 0.8684 0.02033 0.01415 0.0179 0.0184 0.8934
10.000 0.8792 0.02118 0.01507 0.0198 0.0182 0.9022
10.250 0.8935 0.02182 0.01579 0.0212 0.0179 0.9124
10.500 0.9064 0.02250 0.01657 0.0228 0.0177 0.9248
10.750 0.9197 0.02320 0.01736 0.0243 0.0173 0.9418
11.000 0.9413 0.02399 0.01825 0.0239 0.0170 0.9628
11.250 0.9707 0.02502 0.01932 0.0215 0.0165 0.9824
11.500 0.9859 0.02596 0.02028 0.0222 0.0163 1.0000
11.750 0.9991 0.02699 0.02133 0.0233 0.0160 1.0000
12.000 1.0128 0.02844 0.02282 0.0245 0.0156 1.0000
12.250 1.0277 0.02928 0.02373 0.0253 0.0154 1.0000
12.500 1.0428 0.03030 0.02484 0.0262 0.0152 1.0000
12.750 1.0579 0.03130 0.02590 0.0270 0.0151 1.0000
13.000 1.0731 0.03242 0.02709 0.0278 0.0150 1.0000
13.250 1.0873 0.03362 0.02839 0.0286 0.0148 1.0000
13.500 1.1008 0.03490 0.02975 0.0294 0.0146 1.0000
13.750 1.1128 0.03630 0.03125 0.0303 0.0144 1.0000
14.000 1.1234 0.03771 0.03274 0.0312 0.0143 1.0000
14.250 1.1337 0.03915 0.03425 0.0321 0.0141 1.0000
14.500 1.1419 0.04093 0.03616 0.0330 0.0140 1.0000
14.750 1.1506 0.04253 0.03782 0.0338 0.0139 1.0000
15.000 1.1585 0.04431 0.03966 0.0346 0.0138 1.0000
15.250 1.1625 0.04632 0.04179 0.0354 0.0137 1.0000
15.500 1.1673 0.04864 0.04418 0.0361 0.0135 1.0000
15.750 1.1665 0.05190 0.04760 0.0369 0.0133 1.0000
16.000 1.1513 0.05706 0.05302 0.0380 0.0132 1.0000
16.250 1.1341 0.06003 0.05618 0.0387 0.0131 1.0000
16.750 1.1107 0.06738 0.06387 0.0385 0.0129 1.0000
17.000 1.0950 0.07244 0.06911 0.0377 0.0129 1.0000
17.250 1.0817 0.07736 0.07418 0.0364 0.0130 1.0000
17.500 1.0627 0.08339 0.08040 0.0342 0.0129 1.0000
17.750 1.0404 0.09052 0.08773 0.0311 0.0128 1.0000
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