XFOIL Version 6.96 Calculated polar for: NPL 9627 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -18.000 -1.1162 0.10722 0.10432 -0.0030 1.0000 0.0067 -17.750 -1.1560 0.09608 0.09302 -0.0090 1.0000 0.0067 -17.500 -1.1949 0.08558 0.08235 -0.0146 1.0000 0.0067 -17.250 -1.2296 0.07605 0.07266 -0.0197 1.0000 0.0066 -17.000 -1.2600 0.06734 0.06378 -0.0246 1.0000 0.0066 -16.750 -1.2831 0.05972 0.05601 -0.0291 1.0000 0.0066 -16.500 -1.3003 0.05297 0.04910 -0.0333 1.0000 0.0066 -16.250 -1.3117 0.04737 0.04335 -0.0368 1.0000 0.0066 -16.000 -1.3188 0.04279 0.03864 -0.0394 1.0000 0.0066 -15.750 -1.3232 0.03903 0.03475 -0.0411 1.0000 0.0066 -15.500 -1.3243 0.03603 0.03163 -0.0419 1.0000 0.0067 -15.250 -1.3240 0.03352 0.02901 -0.0421 1.0000 0.0067 -15.000 -1.3217 0.03143 0.02682 -0.0416 1.0000 0.0067 -14.750 -1.3182 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-0.0168 0.8840 0.0202 -5.000 -0.4551 0.00957 0.00324 -0.0164 0.8672 0.0213 -4.750 -0.4282 0.00945 0.00308 -0.0161 0.8508 0.0226 -4.500 -0.4012 0.00935 0.00291 -0.0158 0.8338 0.0236 -4.250 -0.3742 0.00924 0.00275 -0.0155 0.8155 0.0246 -4.000 -0.3472 0.00915 0.00261 -0.0152 0.7962 0.0261 -3.500 -0.2926 0.00899 0.00233 -0.0148 0.7593 0.0291 -3.250 -0.2653 0.00892 0.00221 -0.0146 0.7381 0.0311 -3.000 -0.2382 0.00886 0.00209 -0.0143 0.7127 0.0345 -2.750 -0.2112 0.00878 0.00196 -0.0141 0.6891 0.0437 -2.250 -0.1599 0.00803 0.00158 -0.0134 0.6527 0.1635 -2.000 -0.1338 0.00775 0.00146 -0.0131 0.6343 0.2174 -1.750 -0.1071 0.00760 0.00138 -0.0129 0.6132 0.2554 -1.500 -0.0799 0.00750 0.00132 -0.0127 0.5928 0.2862 -1.250 -0.0524 0.00742 0.00128 -0.0126 0.5774 0.3121 -1.000 -0.0249 0.00735 0.00125 -0.0125 0.5601 0.3387 -0.750 0.0026 0.00734 0.00123 -0.0124 0.5375 0.3628 -0.500 0.0302 0.00731 0.00121 -0.0123 0.5198 0.3863 -0.250 0.0580 0.00726 0.00120 -0.0123 0.5070 0.4090 0.000 0.0855 0.00716 0.00119 -0.0122 0.4944 0.4443 0.250 0.1128 0.00706 0.00118 -0.0120 0.4804 0.4826 0.500 0.1397 0.00697 0.00118 -0.0118 0.4609 0.5273 0.750 0.1660 0.00692 0.00119 -0.0115 0.4320 0.5795 1.000 0.1923 0.00692 0.00122 -0.0112 0.4040 0.6255 1.250 0.2191 0.00690 0.00126 -0.0110 0.3834 0.6679 1.500 0.2458 0.00690 0.00132 -0.0107 0.3610 0.7063 1.750 0.2721 0.00697 0.00139 -0.0104 0.3340 0.7411 2.000 0.2984 0.00706 0.00147 -0.0100 0.3059 0.7726 2.250 0.3248 0.00716 0.00157 -0.0096 0.2825 0.8004 2.500 0.3512 0.00729 0.00168 -0.0093 0.2568 0.8249 2.750 0.3774 0.00747 0.00180 -0.0089 0.2303 0.8474 3.000 0.4033 0.00766 0.00194 -0.0084 0.2028 0.8675 3.250 0.4292 0.00789 0.00209 -0.0080 0.1735 0.8857 3.500 0.4546 0.00819 0.00228 -0.0075 0.1413 0.9024 4.000 0.5054 0.00881 0.00270 -0.0064 0.0854 0.9331 4.250 0.5325 0.00901 0.00288 -0.0062 0.0779 0.9467 4.500 0.5609 0.00920 0.00305 -0.0063 0.0738 0.9573 4.750 0.5897 0.00940 0.00323 -0.0064 0.0704 0.9674 5.000 0.6216 0.00958 0.00341 -0.0073 0.0689 0.9746 5.250 0.6510 0.00976 0.00358 -0.0076 0.0672 0.9807 5.500 0.6837 0.00997 0.00378 -0.0087 0.0650 0.9840 5.750 0.7155 0.01022 0.00400 -0.0097 0.0624 0.9878 6.000 0.7470 0.01041 0.00419 -0.0106 0.0613 0.9910 6.250 0.7786 0.01060 0.00438 -0.0115 0.0599 0.9931 6.500 0.8116 0.01081 0.00459 -0.0127 0.0585 0.9948 6.750 0.8445 0.01104 0.00481 -0.0139 0.0570 0.9968 7.000 0.8767 0.01129 0.00506 -0.0150 0.0554 0.9988 7.250 0.9067 0.01153 0.00530 -0.0156 0.0542 1.0000 7.500 0.9293 0.01171 0.00550 -0.0146 0.0533 1.0000 7.750 0.9521 0.01191 0.00571 -0.0137 0.0519 1.0000 8.000 0.9748 0.01212 0.00592 -0.0127 0.0503 1.0000 8.250 0.9975 0.01237 0.00616 -0.0118 0.0486 1.0000 8.500 1.0205 0.01260 0.00640 -0.0109 0.0471 1.0000 8.750 1.0436 0.01283 0.00665 -0.0101 0.0450 1.0000 9.000 1.0667 0.01311 0.00690 -0.0093 0.0423 1.0000 9.250 1.0900 0.01339 0.00718 -0.0085 0.0390 1.0000 9.500 1.1130 0.01372 0.00749 -0.0078 0.0362 1.0000 9.750 1.1360 0.01407 0.00783 -0.0071 0.0341 1.0000 10.000 1.1587 0.01443 0.00820 -0.0063 0.0324 1.0000 10.250 1.1816 0.01480 0.00858 -0.0056 0.0310 1.0000 10.500 1.2039 0.01520 0.00899 -0.0049 0.0298 1.0000 10.750 1.2258 0.01563 0.00944 -0.0041 0.0286 1.0000 11.000 1.2482 0.01602 0.00986 -0.0033 0.0278 1.0000 11.250 1.2700 0.01644 0.01031 -0.0025 0.0270 1.0000 11.500 1.2912 0.01690 0.01079 -0.0017 0.0263 1.0000 11.750 1.3118 0.01738 0.01130 -0.0008 0.0257 1.0000 12.000 1.3316 0.01791 0.01185 0.0002 0.0250 1.0000 12.250 1.3517 0.01838 0.01237 0.0012 0.0246 1.0000 12.500 1.3713 0.01886 0.01290 0.0022 0.0242 1.0000 12.750 1.3900 0.01938 0.01347 0.0033 0.0238 1.0000 13.000 1.4069 0.01993 0.01406 0.0047 0.0233 1.0000 13.250 1.4215 0.02051 0.01469 0.0065 0.0228 1.0000 13.500 1.4352 0.02117 0.01539 0.0082 0.0223 1.0000 13.750 1.4480 0.02191 0.01618 0.0099 0.0219 1.0000 14.000 1.4597 0.02275 0.01707 0.0116 0.0215 1.0000 14.250 1.4731 0.02351 0.01790 0.0130 0.0212 1.0000 14.500 1.4856 0.02437 0.01883 0.0143 0.0208 1.0000 14.750 1.4971 0.02533 0.01986 0.0155 0.0204 1.0000 15.000 1.5079 0.02641 0.02101 0.0167 0.0200 1.0000 15.250 1.5175 0.02763 0.02229 0.0177 0.0196 1.0000 15.500 1.5261 0.02901 0.02373 0.0185 0.0191 1.0000 15.750 1.5335 0.03057 0.02536 0.0192 0.0187 1.0000 16.000 1.5396 0.03234 0.02721 0.0197 0.0183 1.0000 16.250 1.5462 0.03416 0.02911 0.0200 0.0181 1.0000 16.500 1.5515 0.03619 0.03123 0.0200 0.0177 1.0000 16.750 1.5555 0.03846 0.03359 0.0199 0.0173 1.0000 17.000 1.5579 0.04098 0.03620 0.0196 0.0169 1.0000 17.250 1.5585 0.04380 0.03910 0.0190 0.0166 1.0000 17.500 1.5573 0.04691 0.04230 0.0183 0.0162 1.0000 17.750 1.5538 0.05039 0.04587 0.0173 0.0159 1.0000 18.000 1.5478 0.05424 0.04982 0.0160 0.0156 1.0000 18.250 1.5408 0.05835 0.05404 0.0146 0.0154 1.0000 18.500 1.5312 0.06288 0.05868 0.0129 0.0152 1.0000 18.750 1.5196 0.06783 0.06375 0.0110 0.0150 1.0000 19.000 1.5060 0.07319 0.06922 0.0087 0.0148 1.0000 19.250 1.4893 0.07913 0.07528 0.0061 0.0147 1.0000