NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NLF(1)-0115 (nlf0115-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.42 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf0115-il-1000000.txt Download as CSV file: xf-nlf0115-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NLF(1)-0115
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4800 0.08618 0.08456 -0.0530 1.0000 0.0148
-11.000 -0.5186 0.06953 0.06779 -0.0681 0.9983 0.0147
-10.750 -0.5411 0.06138 0.05948 -0.0746 0.9959 0.0148
-10.500 -0.5578 0.05514 0.05307 -0.0788 0.9930 0.0151
-10.250 -0.5671 0.05045 0.04820 -0.0809 0.9888 0.0150
-10.000 -0.5712 0.04549 0.04300 -0.0827 0.9852 0.0155
-9.750 -0.5579 0.02182 0.01863 -0.0832 0.9748 0.0174
-9.500 -0.5420 0.02018 0.01696 -0.0830 0.9697 0.0176
-9.250 -0.5313 0.01880 0.01550 -0.0816 0.9615 0.0178
-9.000 -0.5244 0.01731 0.01389 -0.0793 0.9504 0.0180
-8.750 -0.5535 0.02059 0.01576 -0.0764 0.9553 0.0136
-8.500 -0.5323 0.01943 0.01445 -0.0755 0.9468 0.0136
-8.250 -0.5117 0.01827 0.01317 -0.0744 0.9354 0.0136
-8.000 -0.4884 0.01728 0.01207 -0.0738 0.9212 0.0136
-7.750 -0.4639 0.01620 0.01087 -0.0734 0.9013 0.0137
-7.500 -0.4411 0.01539 0.00992 -0.0726 0.8737 0.0139
-7.250 -0.4199 0.01481 0.00919 -0.0715 0.8487 0.0140
-7.000 -0.3994 0.01423 0.00849 -0.0703 0.8282 0.0142
-6.750 -0.3790 0.01372 0.00787 -0.0691 0.8115 0.0144
-6.500 -0.3584 0.01328 0.00735 -0.0679 0.7972 0.0148
-6.250 -0.3378 0.01285 0.00684 -0.0667 0.7848 0.0151
-6.000 -0.3173 0.01244 0.00636 -0.0655 0.7739 0.0153
-5.750 -0.2961 0.01208 0.00593 -0.0644 0.7640 0.0157
-5.500 -0.2744 0.01173 0.00553 -0.0634 0.7557 0.0160
-5.250 -0.2523 0.01142 0.00515 -0.0624 0.7480 0.0163
-5.000 -0.2298 0.01112 0.00480 -0.0616 0.7415 0.0165
-4.750 -0.2061 0.01087 0.00451 -0.0609 0.7352 0.0168
-4.500 -0.1855 0.01043 0.00399 -0.0597 0.7294 0.0173
-4.250 -0.1622 0.01011 0.00364 -0.0590 0.7244 0.0180
-4.000 -0.1378 0.00988 0.00339 -0.0584 0.7192 0.0189
-3.750 -0.1129 0.00971 0.00318 -0.0580 0.7145 0.0202
-3.500 -0.0873 0.00956 0.00300 -0.0576 0.7103 0.0210
-3.250 -0.0621 0.00932 0.00276 -0.0572 0.7063 0.0235
-3.000 -0.0363 0.00916 0.00260 -0.0569 0.7025 0.0275
-2.750 -0.0141 0.00873 0.00238 -0.0561 0.6988 0.0846
-2.500 0.0043 0.00797 0.00211 -0.0548 0.6954 0.2299
-2.250 0.0105 0.00620 0.00167 -0.0516 0.6922 0.6052
-2.000 0.0383 0.00626 0.00176 -0.0516 0.6890 0.6360
-1.750 0.0664 0.00637 0.00185 -0.0515 0.6859 0.6510
-1.500 0.0946 0.00647 0.00190 -0.0516 0.6829 0.6602
-1.250 0.1230 0.00662 0.00204 -0.0516 0.6800 0.6696
-1.000 0.1512 0.00670 0.00213 -0.0516 0.6778 0.6781
-0.750 0.1796 0.00682 0.00226 -0.0517 0.6752 0.6851
-0.500 0.2080 0.00693 0.00233 -0.0517 0.6719 0.6898
-0.250 0.2359 0.00691 0.00225 -0.0518 0.6661 0.6912
0.000 0.2638 0.00687 0.00220 -0.0518 0.6596 0.6920
0.250 0.2914 0.00685 0.00214 -0.0519 0.6526 0.6928
0.500 0.3192 0.00685 0.00211 -0.0519 0.6457 0.6935
0.750 0.3472 0.00683 0.00209 -0.0520 0.6397 0.6943
1.000 0.3751 0.00686 0.00207 -0.0520 0.6345 0.6950
1.250 0.4033 0.00687 0.00208 -0.0522 0.6303 0.6959
1.500 0.4316 0.00686 0.00208 -0.0524 0.6256 0.6968
1.750 0.4594 0.00689 0.00209 -0.0524 0.6204 0.6978
2.000 0.4872 0.00692 0.00210 -0.0525 0.6156 0.6987
2.250 0.5153 0.00692 0.00212 -0.0526 0.6095 0.6996
2.500 0.5425 0.00696 0.00213 -0.0526 0.6030 0.7004
2.750 0.5703 0.00697 0.00215 -0.0527 0.5963 0.7013
3.000 0.5972 0.00702 0.00217 -0.0525 0.5873 0.7022
3.250 0.6244 0.00705 0.00220 -0.0525 0.5770 0.7031
3.500 0.6509 0.00710 0.00224 -0.0523 0.5651 0.7039
3.750 0.6767 0.00719 0.00228 -0.0520 0.5468 0.7047
4.000 0.6987 0.00740 0.00234 -0.0509 0.5076 0.7054
4.250 0.7132 0.00796 0.00256 -0.0485 0.4309 0.7069
4.500 0.7289 0.00853 0.00285 -0.0464 0.3678 0.7082
4.750 0.7464 0.00900 0.00312 -0.0447 0.3195 0.7095
5.000 0.7647 0.00943 0.00337 -0.0431 0.2805 0.7109
5.250 0.7846 0.00977 0.00359 -0.0418 0.2528 0.7123
5.750 0.8254 0.01035 0.00401 -0.0393 0.2149 0.7150
6.000 0.8458 0.01062 0.00422 -0.0381 0.1995 0.7163
6.500 0.8843 0.01110 0.00462 -0.0352 0.1760 0.7191
6.750 0.9029 0.01133 0.00482 -0.0336 0.1668 0.7204
7.000 0.9206 0.01162 0.00507 -0.0319 0.1573 0.7217
7.250 0.9399 0.01184 0.00530 -0.0305 0.1500 0.7238
7.500 0.9575 0.01214 0.00558 -0.0288 0.1423 0.7257
7.750 0.9772 0.01237 0.00584 -0.0275 0.1372 0.7276
8.000 0.9948 0.01269 0.00614 -0.0259 0.1304 0.7296
8.250 1.0136 0.01297 0.00644 -0.0245 0.1253 0.7317
8.500 1.0321 0.01327 0.00674 -0.0231 0.1205 0.7338
8.750 1.0485 0.01366 0.00711 -0.0214 0.1146 0.7360
9.000 1.0676 0.01394 0.00742 -0.0201 0.1114 0.7384
9.250 1.0851 0.01426 0.00777 -0.0187 0.1071 0.7415
9.500 1.1004 0.01469 0.00820 -0.0169 0.1016 0.7447
9.750 1.1184 0.01502 0.00858 -0.0156 0.0989 0.7481
10.000 1.1360 0.01538 0.00896 -0.0142 0.0953 0.7515
10.250 1.1508 0.01586 0.00943 -0.0125 0.0901 0.7552
10.500 1.1666 0.01629 0.00993 -0.0110 0.0872 0.7596
10.750 1.1836 0.01669 0.01037 -0.0097 0.0838 0.7647
11.000 1.1982 0.01722 0.01090 -0.0082 0.0796 0.7700
11.250 1.2111 0.01782 0.01154 -0.0064 0.0760 0.7769
11.750 1.2421 0.01878 0.01265 -0.0037 0.0707 0.7959
12.000 1.2539 0.01946 0.01337 -0.0020 0.0667 0.8110
12.250 1.2664 0.02002 0.01407 -0.0003 0.0643 0.8358
12.500 1.2869 0.02038 0.01478 -0.0001 0.0616 0.9400
12.750 1.3132 0.02129 0.01568 -0.0019 0.0574 1.0000
13.000 1.3259 0.02214 0.01656 -0.0007 0.0546 1.0000
13.250 1.3404 0.02289 0.01734 0.0003 0.0520 1.0000
13.500 1.3522 0.02384 0.01829 0.0014 0.0493 1.0000
13.750 1.3626 0.02492 0.01937 0.0026 0.0462 1.0000
14.000 1.3764 0.02577 0.02027 0.0035 0.0447 1.0000
14.250 1.3880 0.02679 0.02133 0.0045 0.0426 1.0000
14.500 1.3980 0.02796 0.02251 0.0055 0.0403 1.0000
14.750 1.4077 0.02918 0.02376 0.0064 0.0381 1.0000
15.000 1.4193 0.03027 0.02490 0.0072 0.0364 1.0000
15.250 1.4288 0.03154 0.02621 0.0080 0.0347 1.0000
15.500 1.4357 0.03306 0.02773 0.0090 0.0321 1.0000
15.750 1.4451 0.03440 0.02912 0.0096 0.0302 1.0000
16.000 1.4519 0.03598 0.03073 0.0104 0.0277 1.0000
16.250 1.4573 0.03773 0.03250 0.0111 0.0252 1.0000
16.500 1.4631 0.03946 0.03428 0.0117 0.0230 1.0000
16.750 1.4640 0.04170 0.03653 0.0124 0.0191 1.0000
17.000 1.4619 0.04430 0.03914 0.0130 0.0150 1.0000
17.250 1.4609 0.04686 0.04173 0.0134 0.0129 1.0000
17.500 1.4553 0.04999 0.04491 0.0137 0.0104 1.0000
17.750 1.4526 0.05294 0.04793 0.0138 0.0093 1.0000
18.000 1.4505 0.05591 0.05098 0.0137 0.0089 1.0000
18.250 1.4439 0.05951 0.05467 0.0134 0.0080 1.0000
18.500 1.4411 0.06277 0.05803 0.0129 0.0078 1.0000
18.750 1.4349 0.06659 0.06196 0.0122 0.0074 1.0000
19.000 1.4277 0.07068 0.06615 0.0112 0.0072 1.0000
19.250 1.4199 0.07499 0.07057 0.0099 0.0071 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NLF(1)-0115 (nlf0115-il)