NACA 66-018 (naca66-018-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66-018 (naca66-018-il) Reynolds number: 200,000 Max Cl/Cd: 34.45 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66-018-il-200000-n5.txt Download as CSV file: xf-naca66-018-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-018
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.7162 0.12403 0.11987 -0.0453 1.0000 0.0203
-17.750 -0.7477 0.11271 0.10839 -0.0521 1.0000 0.0202
-17.500 -0.7783 0.10260 0.09806 -0.0581 1.0000 0.0201
-17.250 -0.8063 0.09390 0.08914 -0.0629 1.0000 0.0200
-17.000 -0.8290 0.08675 0.08177 -0.0664 1.0000 0.0200
-16.750 -0.8473 0.08077 0.07559 -0.0689 1.0000 0.0200
-16.500 -0.8687 0.07484 0.06939 -0.0708 1.0000 0.0201
-16.250 -0.8842 0.07000 0.06430 -0.0719 1.0000 0.0202
-16.000 -0.8956 0.06589 0.05997 -0.0724 1.0000 0.0202
-15.750 -0.9064 0.06211 0.05595 -0.0726 1.0000 0.0203
-15.500 -0.9055 0.05968 0.05349 -0.0722 0.9925 0.0206
-15.250 -0.8998 0.05697 0.05062 -0.0739 0.9629 0.0208
-15.000 -0.8902 0.05458 0.04808 -0.0756 0.9523 0.0212
-14.750 -0.8822 0.05207 0.04536 -0.0766 0.9430 0.0214
-14.500 -0.8744 0.04989 0.04300 -0.0770 0.9340 0.0218
-14.250 -0.8668 0.04793 0.04086 -0.0768 0.9255 0.0221
-14.000 -0.8577 0.04611 0.03884 -0.0764 0.9182 0.0225
-13.750 -0.8477 0.04443 0.03697 -0.0758 0.9111 0.0228
-13.500 -0.8349 0.04290 0.03526 -0.0753 0.9048 0.0230
-13.250 -0.8213 0.04147 0.03364 -0.0747 0.8992 0.0235
-13.000 -0.8063 0.04018 0.03218 -0.0741 0.8935 0.0239
-12.750 -0.7908 0.03897 0.03080 -0.0734 0.8884 0.0244
-12.500 -0.7726 0.03790 0.02968 -0.0730 0.8842 0.0247
-12.250 -0.7567 0.03687 0.02862 -0.0725 0.8794 0.0252
-12.000 -0.7414 0.03591 0.02760 -0.0718 0.8749 0.0257
-11.750 -0.7263 0.03499 0.02662 -0.0710 0.8710 0.0265
-11.500 -0.7109 0.03412 0.02563 -0.0703 0.8676 0.0274
-11.250 -0.6946 0.03323 0.02466 -0.0696 0.8636 0.0281
-11.000 -0.6787 0.03239 0.02373 -0.0688 0.8598 0.0290
-10.750 -0.6655 0.03141 0.02274 -0.0678 0.8563 0.0298
-10.500 -0.6518 0.03055 0.02183 -0.0667 0.8532 0.0306
-10.250 -0.6380 0.02971 0.02094 -0.0656 0.8503 0.0314
-10.000 -0.6242 0.02887 0.02005 -0.0646 0.8469 0.0325
-9.750 -0.6102 0.02808 0.01918 -0.0634 0.8435 0.0338
-9.500 -0.5982 0.02721 0.01828 -0.0621 0.8404 0.0352
-9.250 -0.5848 0.02646 0.01750 -0.0609 0.8375 0.0368
-9.000 -0.5707 0.02578 0.01675 -0.0596 0.8349 0.0389
-8.750 -0.5571 0.02506 0.01598 -0.0583 0.8321 0.0412
-8.500 -0.5432 0.02436 0.01527 -0.0571 0.8289 0.0439
-8.250 -0.5279 0.02376 0.01461 -0.0559 0.8261 0.0471
-8.000 -0.5145 0.02307 0.01395 -0.0545 0.8235 0.0525
-7.750 -0.5006 0.02242 0.01331 -0.0530 0.8211 0.0602
-7.500 -0.4876 0.02174 0.01267 -0.0514 0.8189 0.0737
-7.250 -0.4780 0.02093 0.01200 -0.0494 0.8170 0.1005
-7.000 -0.4731 0.01993 0.01130 -0.0468 0.8144 0.1523
-6.750 -0.4713 0.01888 0.01059 -0.0438 0.8115 0.2135
-6.500 -0.4731 0.01780 0.00985 -0.0400 0.8086 0.2764
-6.250 -0.4776 0.01676 0.00910 -0.0356 0.8058 0.3379
-6.000 -0.4851 0.01575 0.00839 -0.0303 0.8032 0.3993
-5.750 -0.4930 0.01490 0.00785 -0.0245 0.8008 0.4610
-5.500 -0.4978 0.01445 0.00784 -0.0186 0.7986 0.5363
-5.250 -0.4481 0.01560 0.00943 -0.0211 0.7977 0.6299
-5.000 -0.4546 0.01559 0.00941 -0.0150 0.7944 0.6550
-4.750 -0.4521 0.01580 0.00959 -0.0103 0.7917 0.6788
-4.500 -0.4411 0.01624 0.00998 -0.0069 0.7896 0.6976
-4.250 -0.3910 0.01743 0.01115 -0.0100 0.7890 0.7052
-4.000 -0.3850 0.01725 0.01087 -0.0064 0.7869 0.7151
-3.750 -0.3438 0.01787 0.01145 -0.0084 0.7861 0.7179
-3.500 -0.3085 0.01831 0.01183 -0.0096 0.7852 0.7211
-3.250 -0.2975 0.01811 0.01155 -0.0069 0.7837 0.7287
-3.000 -0.2744 0.01810 0.01147 -0.0063 0.7827 0.7325
-2.750 -0.2423 0.01829 0.01161 -0.0071 0.7819 0.7341
-2.500 -0.2142 0.01848 0.01178 -0.0074 0.7802 0.7360
-2.250 -0.1898 0.01863 0.01192 -0.0071 0.7780 0.7386
-2.000 -0.1739 0.01858 0.01184 -0.0055 0.7758 0.7432
-1.750 -0.1650 0.01831 0.01151 -0.0028 0.7736 0.7487
-1.500 -0.1371 0.01844 0.01164 -0.0031 0.7722 0.7500
-1.250 -0.1104 0.01854 0.01173 -0.0032 0.7708 0.7514
-1.000 -0.0844 0.01859 0.01176 -0.0031 0.7695 0.7530
-0.750 -0.0595 0.01857 0.01172 -0.0029 0.7681 0.7549
-0.500 -0.0362 0.01850 0.01164 -0.0024 0.7669 0.7573
-0.250 -0.0156 0.01837 0.01147 -0.0016 0.7658 0.7604
0.000 0.0003 0.01803 0.01107 0.0000 0.7645 0.7645
0.250 0.0163 0.01831 0.01140 0.0015 0.7607 0.7659
0.500 0.0359 0.01848 0.01161 0.0025 0.7574 0.7670
0.750 0.0588 0.01856 0.01171 0.0030 0.7549 0.7682
1.000 0.0836 0.01859 0.01176 0.0032 0.7529 0.7695
1.250 0.1094 0.01855 0.01174 0.0033 0.7512 0.7709
1.500 0.1361 0.01846 0.01166 0.0032 0.7498 0.7722
1.750 0.1639 0.01833 0.01154 0.0030 0.7484 0.7736
2.250 0.1902 0.01865 0.01194 0.0071 0.7386 0.7778
2.500 0.2140 0.01852 0.01183 0.0075 0.7359 0.7799
2.750 0.2412 0.01831 0.01163 0.0073 0.7339 0.7820
3.000 0.2730 0.01812 0.01149 0.0065 0.7323 0.7828
3.250 0.3076 0.01785 0.01127 0.0053 0.7308 0.7836
3.500 0.3083 0.01830 0.01182 0.0096 0.7210 0.7853
3.750 0.3428 0.01788 0.01146 0.0086 0.7177 0.7862
4.000 0.3837 0.01728 0.01090 0.0066 0.7149 0.7870
4.250 0.3908 0.01744 0.01116 0.0100 0.7053 0.7890
4.500 0.4414 0.01622 0.00996 0.0069 0.6976 0.7896
4.750 0.4523 0.01578 0.00957 0.0103 0.6785 0.7917
5.000 0.4546 0.01558 0.00940 0.0151 0.6544 0.7943
5.250 0.4489 0.01559 0.00943 0.0210 0.6298 0.7975
5.500 0.4978 0.01445 0.00781 0.0186 0.5319 0.7985
5.750 0.4929 0.01491 0.00785 0.0245 0.4603 0.8009
6.000 0.4844 0.01577 0.00840 0.0304 0.3973 0.8033
6.250 0.4770 0.01678 0.00911 0.0357 0.3359 0.8059
6.500 0.4721 0.01785 0.00987 0.0401 0.2733 0.8086
6.750 0.4711 0.01890 0.01060 0.0438 0.2119 0.8115
7.000 0.4735 0.01992 0.01130 0.0468 0.1524 0.8144
7.250 0.4783 0.02093 0.01199 0.0493 0.1002 0.8171
7.500 0.4879 0.02175 0.01267 0.0514 0.0731 0.8190
7.750 0.5009 0.02242 0.01331 0.0530 0.0597 0.8211
8.000 0.5147 0.02308 0.01395 0.0544 0.0521 0.8235
8.250 0.5284 0.02375 0.01460 0.0558 0.0470 0.8261
8.500 0.5435 0.02436 0.01527 0.0570 0.0436 0.8288
8.750 0.5576 0.02506 0.01598 0.0582 0.0411 0.8319
9.000 0.5710 0.02579 0.01675 0.0595 0.0390 0.8350
9.250 0.5848 0.02649 0.01753 0.0608 0.0371 0.8375
9.500 0.5985 0.02722 0.01830 0.0621 0.0352 0.8404
9.750 0.6103 0.02810 0.01920 0.0634 0.0339 0.8436
10.000 0.6245 0.02888 0.02006 0.0645 0.0325 0.8469
10.250 0.6386 0.02970 0.02093 0.0655 0.0315 0.8503
10.500 0.6525 0.03053 0.02181 0.0666 0.0304 0.8533
10.750 0.6662 0.03140 0.02273 0.0677 0.0297 0.8564
11.000 0.6797 0.03234 0.02369 0.0687 0.0290 0.8599
11.250 0.6952 0.03324 0.02464 0.0695 0.0283 0.8636
11.500 0.7115 0.03409 0.02561 0.0702 0.0274 0.8676
11.750 0.7271 0.03497 0.02659 0.0709 0.0264 0.8712
12.000 0.7422 0.03589 0.02759 0.0717 0.0257 0.8750
12.250 0.7573 0.03686 0.02861 0.0724 0.0251 0.8795
12.500 0.7737 0.03790 0.02967 0.0729 0.0246 0.8841
12.750 0.7914 0.03897 0.03079 0.0733 0.0243 0.8885
13.000 0.8071 0.04014 0.03213 0.0739 0.0238 0.8936
13.250 0.8226 0.04142 0.03358 0.0745 0.0235 0.8994
13.500 0.8363 0.04286 0.03520 0.0751 0.0231 0.9050
13.750 0.8481 0.04442 0.03697 0.0757 0.0226 0.9115
14.000 0.8589 0.04612 0.03885 0.0763 0.0224 0.9185
14.250 0.8682 0.04796 0.04089 0.0766 0.0221 0.9259
14.500 0.8757 0.04997 0.04310 0.0768 0.0218 0.9343
14.750 0.8832 0.05220 0.04553 0.0764 0.0215 0.9435
15.000 0.8914 0.05464 0.04814 0.0753 0.0211 0.9529
15.250 0.9004 0.05717 0.05084 0.0736 0.0208 0.9636
15.500 0.9043 0.05977 0.05359 0.0726 0.0206 1.0000
15.750 0.9038 0.06246 0.05638 0.0724 0.0204 1.0000
16.000 0.8974 0.06584 0.05991 0.0722 0.0202 1.0000
16.250 0.8859 0.06997 0.06426 0.0716 0.0201 1.0000
16.500 0.8737 0.07438 0.06888 0.0706 0.0201 1.0000
16.750 0.8567 0.07969 0.07442 0.0690 0.0201 1.0000
17.000 0.8341 0.08620 0.08118 0.0664 0.0200 1.0000
17.250 0.8121 0.09318 0.08838 0.0630 0.0200 1.0000
17.500 0.7885 0.10100 0.09640 0.0588 0.0201 1.0000
17.750 0.7550 0.11153 0.10717 0.0526 0.0201 1.0000
18.000 0.7148 0.12485 0.12069 0.0445 0.0202 1.0000
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