NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66(2)-415 (naca662415-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.64 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca662415-il-1000000-n5.txt Download as CSV file: xf-naca662415-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-415
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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.9572 0.06429 0.06165 -0.0911 1.0000 0.0099
-17.500 -0.9799 0.05730 0.05449 -0.0951 1.0000 0.0100
-17.000 -1.0058 0.04851 0.04543 -0.0976 0.9908 0.0101
-16.750 -0.9984 0.04468 0.04144 -0.1019 0.9764 0.0103
-16.500 -0.9873 0.04111 0.03769 -0.1064 0.9697 0.0104
-16.250 -0.9719 0.03800 0.03439 -0.1107 0.9632 0.0106
-16.000 -0.9510 0.03556 0.03179 -0.1149 0.9555 0.0107
-15.750 -0.9302 0.03340 0.02944 -0.1184 0.9455 0.0108
-15.500 -0.9174 0.03140 0.02725 -0.1201 0.9306 0.0109
-15.250 -0.9103 0.02988 0.02558 -0.1197 0.9157 0.0110
-15.000 -0.9055 0.02851 0.02407 -0.1186 0.9035 0.0112
-14.750 -0.8976 0.02742 0.02287 -0.1174 0.8935 0.0114
-14.500 -0.8894 0.02641 0.02175 -0.1161 0.8848 0.0115
-14.250 -0.8784 0.02556 0.02083 -0.1150 0.8772 0.0117
-13.750 -0.8538 0.02412 0.01922 -0.1128 0.8641 0.0120
-13.500 -0.8389 0.02360 0.01865 -0.1118 0.8580 0.0123
-13.250 -0.8277 0.02277 0.01771 -0.1104 0.8523 0.0124
-13.000 -0.8152 0.02198 0.01682 -0.1091 0.8469 0.0126
-12.750 -0.8009 0.02138 0.01613 -0.1079 0.8414 0.0128
-12.500 -0.7867 0.02073 0.01539 -0.1066 0.8366 0.0131
-12.250 -0.7720 0.02007 0.01465 -0.1054 0.8322 0.0132
-12.000 -0.7565 0.01949 0.01397 -0.1043 0.8278 0.0134
-11.750 -0.7413 0.01888 0.01326 -0.1029 0.8236 0.0136
-11.500 -0.7250 0.01834 0.01264 -0.1018 0.8200 0.0137
-11.250 -0.7104 0.01766 0.01190 -0.1004 0.8164 0.0139
-11.000 -0.6948 0.01708 0.01127 -0.0990 0.8126 0.0142
-10.750 -0.6769 0.01669 0.01084 -0.0979 0.8091 0.0145
-10.250 -0.6404 0.01593 0.00999 -0.0958 0.8031 0.0151
-10.000 -0.6219 0.01556 0.00958 -0.0947 0.8001 0.0154
-9.750 -0.6044 0.01514 0.00911 -0.0933 0.7969 0.0156
-9.500 -0.5868 0.01477 0.00869 -0.0920 0.7939 0.0159
-9.250 -0.5700 0.01443 0.00829 -0.0904 0.7909 0.0162
-9.000 -0.5525 0.01410 0.00791 -0.0889 0.7883 0.0164
-8.750 -0.5320 0.01383 0.00759 -0.0880 0.7857 0.0168
-8.500 -0.5109 0.01353 0.00725 -0.0872 0.7831 0.0170
-8.250 -0.4917 0.01308 0.00677 -0.0860 0.7805 0.0174
-8.000 -0.4707 0.01275 0.00641 -0.0852 0.7781 0.0178
-7.750 -0.4487 0.01248 0.00611 -0.0845 0.7759 0.0182
-7.500 -0.4260 0.01224 0.00584 -0.0839 0.7738 0.0186
-7.250 -0.4028 0.01198 0.00556 -0.0834 0.7720 0.0190
-7.000 -0.3792 0.01173 0.00530 -0.0829 0.7701 0.0195
-6.750 -0.3554 0.01149 0.00504 -0.0825 0.7680 0.0200
-6.500 -0.3314 0.01127 0.00478 -0.0821 0.7660 0.0205
-6.250 -0.3068 0.01107 0.00456 -0.0818 0.7641 0.0209
-6.000 -0.2835 0.01078 0.00426 -0.0813 0.7622 0.0218
-5.750 -0.2589 0.01058 0.00405 -0.0810 0.7605 0.0225
-5.500 -0.2339 0.01041 0.00385 -0.0807 0.7587 0.0232
-5.250 -0.2084 0.01023 0.00366 -0.0806 0.7572 0.0240
-5.000 -0.1827 0.01005 0.00348 -0.0805 0.7558 0.0248
-4.750 -0.1566 0.00989 0.00331 -0.0804 0.7541 0.0254
-4.500 -0.1311 0.00969 0.00311 -0.0803 0.7523 0.0265
-4.250 -0.1052 0.00951 0.00295 -0.0802 0.7506 0.0281
-4.000 -0.0789 0.00937 0.00280 -0.0801 0.7489 0.0294
-3.750 -0.0523 0.00924 0.00266 -0.0802 0.7474 0.0306
-3.500 -0.0255 0.00913 0.00254 -0.0802 0.7459 0.0315
-3.250 0.0010 0.00899 0.00240 -0.0802 0.7445 0.0343
-3.000 0.0278 0.00887 0.00229 -0.0803 0.7430 0.0374
-2.750 0.0549 0.00874 0.00219 -0.0804 0.7418 0.0433
-2.500 0.0809 0.00851 0.00207 -0.0804 0.7406 0.0723
-2.250 0.1049 0.00806 0.00192 -0.0802 0.7393 0.1557
-2.000 0.1273 0.00741 0.00174 -0.0799 0.7379 0.2896
-1.750 0.1483 0.00647 0.00147 -0.0795 0.7365 0.4848
-1.500 0.1718 0.00580 0.00139 -0.0793 0.7351 0.6600
-1.250 0.2003 0.00578 0.00144 -0.0796 0.7338 0.6896
-1.000 0.2291 0.00580 0.00148 -0.0799 0.7325 0.7055
-0.750 0.2581 0.00583 0.00151 -0.0803 0.7311 0.7139
-0.500 0.2872 0.00587 0.00152 -0.0807 0.7298 0.7195
-0.250 0.3160 0.00590 0.00158 -0.0811 0.7286 0.7268
0.000 0.3453 0.00596 0.00162 -0.0815 0.7273 0.7317
0.250 0.3745 0.00597 0.00163 -0.0820 0.7262 0.7328
0.500 0.4034 0.00597 0.00164 -0.0824 0.7240 0.7338
0.750 0.4320 0.00597 0.00164 -0.0828 0.7207 0.7349
1.000 0.4605 0.00596 0.00165 -0.0831 0.7172 0.7362
1.250 0.4889 0.00598 0.00166 -0.0834 0.7138 0.7376
1.500 0.5170 0.00599 0.00168 -0.0836 0.7087 0.7390
1.750 0.5450 0.00599 0.00170 -0.0838 0.7029 0.7403
2.000 0.5725 0.00603 0.00171 -0.0839 0.6965 0.7417
2.250 0.5999 0.00604 0.00174 -0.0840 0.6866 0.7430
2.500 0.6266 0.00608 0.00176 -0.0839 0.6746 0.7444
2.750 0.6528 0.00614 0.00180 -0.0838 0.6605 0.7458
3.000 0.6760 0.00628 0.00185 -0.0830 0.6294 0.7473
3.250 0.6796 0.00710 0.00218 -0.0783 0.5251 0.7490
3.750 0.6864 0.00878 0.00306 -0.0694 0.3505 0.7527
4.000 0.6851 0.00950 0.00346 -0.0639 0.2759 0.7549
4.250 0.6895 0.01017 0.00388 -0.0597 0.2177 0.7570
4.500 0.6952 0.01088 0.00434 -0.0560 0.1614 0.7593
4.750 0.7051 0.01150 0.00478 -0.0530 0.1176 0.7616
5.000 0.7151 0.01217 0.00525 -0.0502 0.0751 0.7640
5.250 0.7276 0.01278 0.00571 -0.0479 0.0431 0.7660
5.500 0.7451 0.01318 0.00607 -0.0465 0.0337 0.7679
5.750 0.7646 0.01350 0.00640 -0.0454 0.0309 0.7699
6.000 0.7833 0.01387 0.00676 -0.0441 0.0278 0.7720
6.250 0.8030 0.01420 0.00711 -0.0431 0.0264 0.7743
6.500 0.8227 0.01454 0.00746 -0.0421 0.0251 0.7766
6.750 0.8419 0.01491 0.00785 -0.0410 0.0241 0.7790
7.000 0.8603 0.01533 0.00827 -0.0399 0.0226 0.7813
7.250 0.8795 0.01573 0.00868 -0.0389 0.0216 0.7834
7.500 0.8987 0.01611 0.00909 -0.0379 0.0208 0.7859
7.750 0.9177 0.01650 0.00952 -0.0369 0.0196 0.7885
8.000 0.9362 0.01694 0.00997 -0.0359 0.0187 0.7913
8.250 0.9537 0.01744 0.01048 -0.0347 0.0178 0.7943
8.500 0.9723 0.01789 0.01096 -0.0338 0.0171 0.7971
8.750 0.9908 0.01836 0.01146 -0.0328 0.0164 0.7999
9.000 1.0089 0.01883 0.01196 -0.0318 0.0155 0.8030
9.250 1.0262 0.01935 0.01250 -0.0307 0.0148 0.8066
9.500 1.0431 0.01993 0.01310 -0.0296 0.0140 0.8103
9.750 1.0601 0.02050 0.01372 -0.0285 0.0137 0.8139
10.250 1.0939 0.02166 0.01496 -0.0265 0.0127 0.8208
10.500 1.1102 0.02229 0.01563 -0.0254 0.0123 0.8248
10.750 1.1260 0.02296 0.01634 -0.0243 0.0120 0.8289
11.000 1.1418 0.02366 0.01706 -0.0233 0.0116 0.8328
11.250 1.1554 0.02448 0.01793 -0.0220 0.0112 0.8370
11.500 1.1701 0.02523 0.01875 -0.0209 0.0110 0.8417
11.750 1.1849 0.02602 0.01960 -0.0198 0.0109 0.8465
12.000 1.1989 0.02684 0.02049 -0.0187 0.0107 0.8512
12.250 1.2127 0.02769 0.02141 -0.0176 0.0105 0.8566
12.500 1.2253 0.02864 0.02243 -0.0164 0.0104 0.8625
12.750 1.2386 0.02953 0.02339 -0.0153 0.0101 0.8687
13.000 1.2511 0.03050 0.02443 -0.0142 0.0099 0.8760
13.250 1.2624 0.03156 0.02558 -0.0129 0.0098 0.8839
13.500 1.2741 0.03259 0.02669 -0.0118 0.0097 0.8931
13.750 1.2853 0.03363 0.02782 -0.0106 0.0095 0.9028
14.000 1.2948 0.03484 0.02911 -0.0094 0.0094 0.9137
14.250 1.3052 0.03597 0.03032 -0.0082 0.0092 0.9263
14.500 1.3138 0.03724 0.03169 -0.0070 0.0091 0.9431
14.750 1.3280 0.03881 0.03338 -0.0074 0.0090 0.9708
15.250 1.3404 0.04228 0.03699 -0.0055 0.0087 1.0000
15.500 1.3453 0.04426 0.03906 -0.0046 0.0086 1.0000
15.750 1.3523 0.04610 0.04097 -0.0040 0.0086 1.0000
16.000 1.3593 0.04795 0.04291 -0.0035 0.0085 1.0000
16.250 1.3649 0.04998 0.04503 -0.0030 0.0085 1.0000
16.500 1.3709 0.05204 0.04717 -0.0026 0.0084 1.0000
16.750 1.3732 0.05456 0.04980 -0.0022 0.0084 1.0000
17.000 1.3772 0.05694 0.05227 -0.0020 0.0084 1.0000
17.250 1.3796 0.05958 0.05500 -0.0019 0.0083 1.0000
17.500 1.3804 0.06246 0.05800 -0.0020 0.0083 1.0000
17.750 1.3806 0.06553 0.06117 -0.0022 0.0082 1.0000
18.000 1.3796 0.06886 0.06461 -0.0026 0.0082 1.0000
18.250 1.3778 0.07238 0.06824 -0.0033 0.0081 1.0000
18.500 1.3765 0.07596 0.07193 -0.0041 0.0081 1.0000
18.750 1.3718 0.08010 0.07620 -0.0052 0.0080 1.0000
19.000 1.3678 0.08430 0.08051 -0.0066 0.0080 1.0000
19.250 1.3611 0.08903 0.08536 -0.0083 0.0079 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66(2)-415 (naca662415-il)