NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLF(1)-0115 (nlf0115-il) Reynolds number: 500,000 Max Cl/Cd: 69.47 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf0115-il-500000-n5.txt Download as CSV file: xf-nlf0115-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6252 0.06378 0.06090 -0.0713 1.0000 0.0101
-12.500 -0.6617 0.05729 0.05422 -0.0726 1.0000 0.0101
-12.250 -0.6912 0.05266 0.04943 -0.0718 1.0000 0.0101
-12.000 -0.7103 0.04829 0.04486 -0.0721 0.9990 0.0101
-11.750 -0.7214 0.04359 0.03987 -0.0739 0.9957 0.0101
-11.500 -0.7260 0.03994 0.03596 -0.0747 0.9919 0.0101
-11.250 -0.7246 0.03689 0.03264 -0.0753 0.9879 0.0101
-11.000 -0.7190 0.03377 0.02926 -0.0761 0.9846 0.0102
-10.750 -0.7108 0.03169 0.02698 -0.0756 0.9796 0.0103
-10.500 -0.6945 0.03004 0.02519 -0.0759 0.9754 0.0105
-10.250 -0.6742 0.02787 0.02277 -0.0768 0.9726 0.0105
-10.000 -0.6607 0.02660 0.02136 -0.0755 0.9653 0.0107
-9.750 -0.6373 0.02542 0.02004 -0.0760 0.9607 0.0108
-9.500 -0.6202 0.02451 0.01903 -0.0749 0.9526 0.0111
-9.000 -0.5787 0.02229 0.01654 -0.0739 0.9352 0.0115
-8.750 -0.5557 0.02118 0.01528 -0.0736 0.9240 0.0117
-8.500 -0.5297 0.02009 0.01403 -0.0738 0.9101 0.0119
-8.250 -0.5021 0.01907 0.01285 -0.0742 0.8926 0.0121
-8.000 -0.4759 0.01821 0.01181 -0.0743 0.8719 0.0123
-7.750 -0.4531 0.01751 0.01094 -0.0736 0.8506 0.0125
-7.500 -0.4321 0.01694 0.01021 -0.0726 0.8313 0.0127
-7.250 -0.4118 0.01641 0.00955 -0.0714 0.8151 0.0128
-7.000 -0.3915 0.01597 0.00898 -0.0703 0.8012 0.0130
-6.750 -0.3712 0.01556 0.00846 -0.0691 0.7895 0.0132
-6.500 -0.3537 0.01490 0.00774 -0.0675 0.7788 0.0135
-6.250 -0.3345 0.01442 0.00720 -0.0662 0.7697 0.0138
-6.000 -0.3146 0.01403 0.00675 -0.0650 0.7612 0.0141
-5.750 -0.2937 0.01366 0.00635 -0.0640 0.7537 0.0145
-5.500 -0.2724 0.01333 0.00596 -0.0629 0.7466 0.0149
-5.250 -0.2504 0.01303 0.00561 -0.0620 0.7403 0.0155
-5.000 -0.2280 0.01275 0.00528 -0.0612 0.7338 0.0161
-4.500 -0.1828 0.01217 0.00460 -0.0596 0.7229 0.0173
-4.250 -0.1596 0.01189 0.00430 -0.0588 0.7179 0.0180
-4.000 -0.1358 0.01168 0.00403 -0.0582 0.7135 0.0190
-3.750 -0.1112 0.01148 0.00380 -0.0577 0.7094 0.0203
-3.500 -0.0864 0.01128 0.00358 -0.0573 0.7053 0.0219
-3.250 -0.0618 0.01107 0.00338 -0.0568 0.7013 0.0264
-3.000 -0.0380 0.01082 0.00319 -0.0562 0.6977 0.0459
-2.750 -0.0146 0.01049 0.00300 -0.0556 0.6941 0.0840
-2.500 0.0068 0.00999 0.00279 -0.0548 0.6904 0.1631
-2.250 0.0064 0.00788 0.00227 -0.0507 0.6868 0.5883
-2.000 0.0333 0.00797 0.00238 -0.0504 0.6839 0.6297
-1.750 0.0608 0.00808 0.00246 -0.0502 0.6812 0.6476
-1.500 0.0881 0.00826 0.00265 -0.0500 0.6786 0.6664
-1.250 0.1157 0.00838 0.00276 -0.0498 0.6757 0.6774
-1.000 0.1438 0.00844 0.00280 -0.0498 0.6726 0.6824
-0.750 0.1722 0.00845 0.00276 -0.0500 0.6698 0.6837
-0.500 0.2007 0.00846 0.00272 -0.0502 0.6674 0.6846
-0.250 0.2293 0.00849 0.00269 -0.0504 0.6652 0.6854
0.000 0.2578 0.00849 0.00267 -0.0507 0.6627 0.6863
0.250 0.2859 0.00849 0.00265 -0.0508 0.6587 0.6872
0.500 0.3132 0.00851 0.00261 -0.0507 0.6515 0.6883
0.750 0.3401 0.00852 0.00258 -0.0506 0.6424 0.6892
1.000 0.3668 0.00855 0.00253 -0.0504 0.6332 0.6900
1.250 0.3935 0.00853 0.00252 -0.0502 0.6232 0.6908
1.500 0.4203 0.00856 0.00251 -0.0501 0.6151 0.6916
1.750 0.4475 0.00857 0.00253 -0.0500 0.6075 0.6924
2.000 0.4744 0.00861 0.00254 -0.0499 0.6010 0.6933
2.250 0.5017 0.00863 0.00258 -0.0498 0.5930 0.6942
2.500 0.5281 0.00868 0.00260 -0.0496 0.5844 0.6951
2.750 0.5548 0.00871 0.00264 -0.0495 0.5743 0.6961
3.000 0.5807 0.00877 0.00269 -0.0491 0.5607 0.6972
3.250 0.6050 0.00886 0.00272 -0.0485 0.5401 0.6983
3.500 0.6273 0.00903 0.00278 -0.0475 0.5071 0.6996
3.750 0.6421 0.00950 0.00294 -0.0451 0.4422 0.7010
4.000 0.6562 0.01009 0.00324 -0.0427 0.3808 0.7024
4.250 0.6728 0.01060 0.00353 -0.0408 0.3336 0.7036
4.500 0.6913 0.01101 0.00378 -0.0393 0.2992 0.7048
4.750 0.7103 0.01138 0.00403 -0.0378 0.2718 0.7059
5.000 0.7293 0.01171 0.00427 -0.0364 0.2483 0.7071
5.250 0.7485 0.01203 0.00451 -0.0350 0.2285 0.7083
5.500 0.7678 0.01230 0.00474 -0.0335 0.2138 0.7097
5.750 0.7857 0.01257 0.00497 -0.0319 0.2006 0.7111
6.000 0.8040 0.01283 0.00520 -0.0303 0.1887 0.7126
6.250 0.8223 0.01310 0.00545 -0.0287 0.1782 0.7142
6.500 0.8404 0.01341 0.00573 -0.0271 0.1695 0.7158
6.750 0.8594 0.01370 0.00602 -0.0257 0.1615 0.7175
7.000 0.8775 0.01403 0.00633 -0.0242 0.1540 0.7192
7.250 0.8962 0.01435 0.00665 -0.0228 0.1467 0.7210
7.500 0.9137 0.01469 0.00699 -0.0213 0.1405 0.7228
7.750 0.9323 0.01499 0.00734 -0.0199 0.1349 0.7249
8.000 0.9493 0.01537 0.00772 -0.0184 0.1291 0.7272
8.250 0.9672 0.01572 0.00810 -0.0170 0.1241 0.7296
8.500 0.9847 0.01610 0.00850 -0.0156 0.1192 0.7320
8.750 1.0007 0.01655 0.00895 -0.0140 0.1144 0.7345
9.000 1.0185 0.01694 0.00938 -0.0127 0.1104 0.7370
9.250 1.0350 0.01736 0.00985 -0.0112 0.1062 0.7396
9.500 1.0504 0.01786 0.01036 -0.0097 0.1023 0.7426
9.750 1.0664 0.01833 0.01090 -0.0083 0.0989 0.7460
10.000 1.0828 0.01881 0.01143 -0.0070 0.0952 0.7497
10.500 1.1116 0.02000 0.01267 -0.0040 0.0878 0.7576
10.750 1.1275 0.02052 0.01329 -0.0028 0.0849 0.7627
11.000 1.1422 0.02114 0.01396 -0.0015 0.0818 0.7681
11.250 1.1557 0.02182 0.01469 -0.0001 0.0788 0.7740
11.500 1.1684 0.02258 0.01551 0.0013 0.0758 0.7815
11.750 1.1831 0.02321 0.01624 0.0025 0.0729 0.7902
12.250 1.2072 0.02480 0.01798 0.0052 0.0662 0.8169
12.500 1.2192 0.02555 0.01887 0.0066 0.0636 0.8403
12.750 1.2390 0.02629 0.01987 0.0063 0.0593 0.9131
13.000 1.2622 0.02744 0.02107 0.0046 0.0556 1.0000
13.250 1.2749 0.02842 0.02210 0.0055 0.0533 1.0000
13.500 1.2868 0.02949 0.02322 0.0063 0.0504 1.0000
13.750 1.2973 0.03068 0.02444 0.0072 0.0480 1.0000
14.000 1.3073 0.03192 0.02571 0.0080 0.0455 1.0000
14.250 1.3179 0.03315 0.02699 0.0088 0.0429 1.0000
14.500 1.3275 0.03448 0.02836 0.0095 0.0409 1.0000
14.750 1.3350 0.03602 0.02992 0.0103 0.0381 1.0000
15.000 1.3442 0.03744 0.03141 0.0109 0.0360 1.0000
15.250 1.3521 0.03899 0.03303 0.0115 0.0342 1.0000
15.500 1.3580 0.04076 0.03483 0.0121 0.0321 1.0000
15.750 1.3648 0.04249 0.03663 0.0125 0.0304 1.0000
16.000 1.3706 0.04435 0.03856 0.0129 0.0283 1.0000
16.250 1.3751 0.04638 0.04065 0.0133 0.0267 1.0000
16.500 1.3785 0.04858 0.04291 0.0135 0.0252 1.0000
16.750 1.3820 0.05082 0.04522 0.0137 0.0232 1.0000
17.000 1.3826 0.05344 0.04790 0.0137 0.0212 1.0000
17.250 1.3837 0.05606 0.05062 0.0136 0.0200 1.0000
17.500 1.3825 0.05904 0.05367 0.0133 0.0179 1.0000
17.750 1.3791 0.06237 0.05708 0.0129 0.0163 1.0000
18.000 1.3760 0.06580 0.06061 0.0122 0.0148 1.0000
18.250 1.3683 0.06994 0.06482 0.0112 0.0131 1.0000
18.500 1.3620 0.07403 0.06903 0.0100 0.0121 1.0000
18.750 1.3506 0.07904 0.07415 0.0083 0.0109 1.0000
19.000 1.3390 0.08431 0.07954 0.0063 0.0102 1.0000
19.250 1.3265 0.08988 0.08524 0.0040 0.0097 1.0000
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Polar data table (+)
Polar graphs
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