NACA 66-018 (naca66-018-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-018 (naca66-018-il) Reynolds number: 500,000 Max Cl/Cd: 57.07 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66-018-il-500000.txt Download as CSV file: xf-naca66-018-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.6689 0.12665 0.12418 -0.0454 1.0000 0.0248
-17.250 -0.6609 0.12440 0.12195 -0.0467 1.0000 0.0251
-17.000 -0.6613 0.11990 0.11745 -0.0494 1.0000 0.0254
-16.750 -0.6670 0.11409 0.11162 -0.0532 1.0000 0.0258
-16.500 -0.8141 0.06448 0.06063 -0.0754 0.9249 0.0209
-16.250 -0.8260 0.06013 0.05614 -0.0760 0.9207 0.0210
-16.000 -0.8402 0.05560 0.05143 -0.0762 0.9170 0.0210
-15.750 -0.8539 0.05105 0.04668 -0.0762 0.9130 0.0211
-15.500 -0.8512 0.04874 0.04433 -0.0760 0.9077 0.0214
-15.250 -0.8593 0.04515 0.04057 -0.0753 0.9035 0.0215
-15.000 -0.8642 0.04193 0.03720 -0.0745 0.8994 0.0216
-14.750 -0.8707 0.03830 0.03334 -0.0734 0.8951 0.0216
-14.500 -0.8717 0.03539 0.03025 -0.0723 0.8907 0.0216
-14.250 -0.8698 0.03286 0.02755 -0.0712 0.8866 0.0217
-14.000 -0.8642 0.03072 0.02528 -0.0702 0.8825 0.0220
-13.750 -0.8565 0.02855 0.02297 -0.0693 0.8784 0.0221
-13.500 -0.8476 0.02674 0.02102 -0.0683 0.8743 0.0223
-13.250 -0.8357 0.02496 0.01909 -0.0674 0.8706 0.0226
-13.000 -0.8618 0.03419 0.02778 -0.0708 0.8807 0.0226
-12.750 -0.8450 0.03313 0.02661 -0.0701 0.8760 0.0231
-12.500 -0.8266 0.03220 0.02556 -0.0695 0.8718 0.0233
-12.250 -0.8093 0.03135 0.02459 -0.0688 0.8678 0.0237
-12.000 -0.7942 0.03055 0.02368 -0.0679 0.8637 0.0241
-11.750 -0.7722 0.02963 0.02270 -0.0676 0.8601 0.0247
-11.500 -0.7524 0.02876 0.02183 -0.0671 0.8566 0.0253
-11.250 -0.7354 0.02801 0.02102 -0.0663 0.8531 0.0256
-11.000 -0.7193 0.02732 0.02031 -0.0654 0.8496 0.0264
-10.750 -0.7031 0.02657 0.01952 -0.0645 0.8462 0.0269
-10.500 -0.6874 0.02582 0.01873 -0.0635 0.8428 0.0274
-10.250 -0.6718 0.02514 0.01798 -0.0625 0.8397 0.0280
-10.000 -0.6556 0.02453 0.01730 -0.0615 0.8368 0.0287
-9.750 -0.6449 0.02359 0.01632 -0.0598 0.8338 0.0297
-9.500 -0.6325 0.02277 0.01550 -0.0584 0.8311 0.0308
-9.250 -0.6180 0.02210 0.01482 -0.0572 0.8283 0.0317
-9.000 -0.6029 0.02148 0.01417 -0.0559 0.8256 0.0329
-8.750 -0.5873 0.02091 0.01354 -0.0547 0.8230 0.0345
-8.500 -0.5764 0.02011 0.01273 -0.0529 0.8205 0.0363
-8.250 -0.5613 0.01956 0.01214 -0.0516 0.8182 0.0380
-8.000 -0.5451 0.01908 0.01162 -0.0503 0.8160 0.0405
-7.750 -0.5323 0.01840 0.01097 -0.0487 0.8139 0.0440
-7.500 -0.5166 0.01788 0.01044 -0.0473 0.8117 0.0483
-7.250 -0.5022 0.01732 0.00991 -0.0458 0.8095 0.0550
-7.000 -0.4923 0.01657 0.00930 -0.0436 0.8072 0.0757
-6.750 -0.4925 0.01544 0.00852 -0.0399 0.8047 0.1378
-6.500 -0.4965 0.01427 0.00773 -0.0356 0.8023 0.2142
-6.250 -0.5021 0.01320 0.00698 -0.0308 0.7999 0.2847
-6.000 -0.5112 0.01216 0.00626 -0.0251 0.7977 0.3502
-5.750 -0.5257 0.01119 0.00560 -0.0181 0.7951 0.4128
-5.500 -0.5422 0.01058 0.00525 -0.0101 0.7925 0.4701
-5.250 -0.5529 0.00984 0.00490 -0.0031 0.7902 0.5476
-5.000 -0.5479 0.00960 0.00504 0.0014 0.7884 0.6365
-4.750 -0.5261 0.00969 0.00510 0.0025 0.7871 0.6632
-4.500 -0.5017 0.00981 0.00519 0.0031 0.7859 0.6788
-4.250 -0.4752 0.00999 0.00534 0.0033 0.7848 0.6900
-4.000 -0.4498 0.01017 0.00548 0.0037 0.7838 0.7006
-3.750 -0.4240 0.01059 0.00586 0.0043 0.7827 0.7136
-3.500 -0.3913 0.01118 0.00651 0.0037 0.7816 0.7234
-3.250 -0.3671 0.01140 0.00669 0.0042 0.7804 0.7312
-3.000 -0.3325 0.01184 0.00719 0.0031 0.7794 0.7363
-2.750 -0.3019 0.01220 0.00756 0.0026 0.7784 0.7411
-2.500 -0.2762 0.01235 0.00768 0.0028 0.7772 0.7460
-2.250 -0.2491 0.01242 0.00773 0.0026 0.7760 0.7492
-2.000 -0.2195 0.01254 0.00786 0.0021 0.7749 0.7510
-1.750 -0.1906 0.01264 0.00796 0.0016 0.7738 0.7527
-1.500 -0.1621 0.01273 0.00805 0.0012 0.7728 0.7545
-1.250 -0.1341 0.01281 0.00811 0.0009 0.7715 0.7567
-1.000 -0.1068 0.01284 0.00813 0.0007 0.7704 0.7591
-0.750 -0.0805 0.01283 0.00810 0.0006 0.7694 0.7612
-0.500 -0.0547 0.01280 0.00803 0.0005 0.7684 0.7632
-0.250 -0.0287 0.01276 0.00796 0.0004 0.7673 0.7649
0.000 -0.0002 0.01268 0.00788 0.0000 0.7661 0.7662
0.250 0.0284 0.01272 0.00791 -0.0004 0.7648 0.7674
0.500 0.0550 0.01278 0.00800 -0.0006 0.7633 0.7685
0.750 0.0807 0.01281 0.00807 -0.0006 0.7614 0.7694
1.000 0.1068 0.01283 0.00811 -0.0007 0.7591 0.7704
1.250 0.1340 0.01280 0.00810 -0.0009 0.7568 0.7715
1.500 0.1619 0.01274 0.00805 -0.0012 0.7545 0.7727
1.750 0.1903 0.01265 0.00797 -0.0016 0.7526 0.7738
2.000 0.2191 0.01255 0.00788 -0.0020 0.7509 0.7749
2.250 0.2487 0.01242 0.00774 -0.0026 0.7491 0.7760
2.500 0.2771 0.01233 0.00765 -0.0029 0.7461 0.7771
2.750 0.3022 0.01220 0.00756 -0.0027 0.7412 0.7783
3.000 0.3323 0.01186 0.00722 -0.0031 0.7363 0.7794
3.250 0.3668 0.01140 0.00669 -0.0042 0.7312 0.7804
3.500 0.3915 0.01119 0.00654 -0.0037 0.7239 0.7816
3.750 0.4244 0.01060 0.00585 -0.0043 0.7136 0.7827
4.000 0.4496 0.01018 0.00548 -0.0037 0.7005 0.7838
4.250 0.4752 0.00999 0.00534 -0.0033 0.6900 0.7849
4.500 0.5020 0.00981 0.00518 -0.0032 0.6791 0.7859
4.750 0.5262 0.00968 0.00509 -0.0025 0.6633 0.7871
5.000 0.5479 0.00960 0.00504 -0.0014 0.6363 0.7884
5.250 0.5533 0.00983 0.00490 0.0030 0.5487 0.7901
5.500 0.5408 0.01061 0.00526 0.0104 0.4671 0.7925
5.750 0.5250 0.01121 0.00561 0.0183 0.4115 0.7951
6.000 0.5117 0.01215 0.00625 0.0251 0.3511 0.7977
6.250 0.5024 0.01322 0.00699 0.0307 0.2845 0.7999
6.500 0.4962 0.01429 0.00773 0.0356 0.2124 0.8023
6.750 0.4921 0.01546 0.00853 0.0400 0.1354 0.8047
7.000 0.4925 0.01657 0.00930 0.0436 0.0753 0.8072
7.250 0.5023 0.01732 0.00992 0.0458 0.0550 0.8094
7.500 0.5167 0.01789 0.01045 0.0473 0.0479 0.8117
7.750 0.5325 0.01840 0.01097 0.0487 0.0437 0.8139
8.000 0.5448 0.01911 0.01164 0.0504 0.0402 0.8161
8.250 0.5616 0.01957 0.01214 0.0515 0.0381 0.8182
8.500 0.5767 0.02011 0.01273 0.0529 0.0363 0.8205
8.750 0.5880 0.02088 0.01351 0.0546 0.0344 0.8230
9.000 0.6028 0.02150 0.01418 0.0559 0.0330 0.8256
9.250 0.6184 0.02210 0.01481 0.0571 0.0318 0.8283
9.500 0.6330 0.02275 0.01549 0.0583 0.0306 0.8312
9.750 0.6459 0.02354 0.01627 0.0597 0.0295 0.8339
10.000 0.6561 0.02452 0.01728 0.0614 0.0286 0.8368
10.250 0.6723 0.02513 0.01797 0.0624 0.0281 0.8397
10.500 0.6879 0.02581 0.01872 0.0635 0.0273 0.8428
10.750 0.7036 0.02655 0.01951 0.0645 0.0269 0.8461
11.000 0.7199 0.02726 0.02025 0.0653 0.0262 0.8496
11.250 0.7365 0.02801 0.02103 0.0662 0.0258 0.8530
11.500 0.7530 0.02874 0.02181 0.0670 0.0253 0.8567
11.750 0.7718 0.02958 0.02266 0.0676 0.0246 0.8602
12.000 0.7992 0.03058 0.02369 0.0674 0.0241 0.8634
12.250 0.8103 0.03135 0.02459 0.0687 0.0236 0.8679
12.500 0.8298 0.03224 0.02559 0.0692 0.0233 0.8717
12.750 0.8474 0.03318 0.02666 0.0699 0.0230 0.8760
13.000 0.8639 0.03421 0.02781 0.0706 0.0227 0.8807
13.250 0.8800 0.03534 0.02904 0.0712 0.0224 0.8855
13.500 0.8950 0.03658 0.03044 0.0721 0.0222 0.8904
13.750 0.9070 0.03780 0.03178 0.0731 0.0218 0.8962
14.000 0.9188 0.03925 0.03335 0.0740 0.0217 0.9023
14.250 0.9280 0.04072 0.03499 0.0751 0.0215 0.9089
14.500 0.9358 0.04230 0.03670 0.0763 0.0214 0.9167
14.750 0.9426 0.04397 0.03853 0.0773 0.0212 0.9251
15.000 0.9469 0.04591 0.04064 0.0783 0.0210 0.9354
15.250 0.9585 0.04748 0.04227 0.0780 0.0207 0.9471
15.500 0.9661 0.05064 0.04568 0.0765 0.0206 0.9565
15.750 0.9733 0.05459 0.04983 0.0744 0.0204 0.9646
16.000 0.9679 0.05950 0.05503 0.0723 0.0203 0.9756
16.250 0.9507 0.06383 0.05957 0.0724 0.0202 1.0000
16.500 0.9384 0.06769 0.06359 0.0722 0.0202 1.0000
16.750 0.9287 0.07105 0.06709 0.0717 0.0203 1.0000
17.000 0.9062 0.07653 0.07276 0.0706 0.0203 1.0000
17.250 0.8881 0.08163 0.07803 0.0688 0.0204 1.0000
17.500 0.8612 0.08845 0.08508 0.0657 0.0206 1.0000
17.750 0.5615 0.16744 0.16502 0.0273 0.0294 1.0000
18.000 0.5708 0.16960 0.16717 0.0263 0.0292 1.0000
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